Pressure distributions on three bodies of revolution to determine the effect of Reynolds number up to and including the ...

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Material Information

Title:
Pressure distributions on three bodies of revolution to determine the effect of Reynolds number up to and including the transonic speed range
Series Title:
NACA RM
Physical Description:
39 p. : ill. ; 28 cm.
Language:
English
Creator:
Swihart, John M
Whitcomb, Charles F
United States -- National Advisory Committee for Aeronautics
Publisher:
NACA
Place of Publication:
Washington, D.C
Publication Date:

Subjects

Subjects / Keywords:
Body of revolution   ( lcsh )
Aerodynamics, Transonic   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Abstract:
Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 10⁶ to 39 x 10⁶, and on maximum diameter from 1.35 x 10⁵ to 4.53 x 10⁵. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Bibliography:
Includes bibliographic references (p. 11).
Statement of Responsibility:
by John M. Swihart and Charles F. Whitcomb.
General Note:
"Report date August 11, 1953."

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 003808074
oclc - 128311695
sobekcm - AA00006179_00001
System ID:
AA00006179:00001

Full Text
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SEARCH MEMORANDUM









"AND INCLUDING THE TRANSONIC SPEED RANGE



kid" Langley Field, Va.
By Jo M. Shart and Charles F. Whitcomb
iLangley Aenautical Laboratory '












UNavERSITY OF FLORIDA
.:DOCUMENTS DEPARTMENT
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NACA RM L5HO04


NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS


RESEARCH MEMORANDUM


PRESSURE DISTRIBUTIONS ON THREE BODIES OF REVOLUTION TO

DETERMINE THE EFFECT OF REYNOLDS NUMBER UP TO

AND INCLUDING THE TRANSONIC SPEED RANGE

By John M. Swihart and Charles F. Whitcomb


SUMMARY


This paper presents the results of an investigation conducted in
the Langley 16-foot transonic tunnel to determine the effects of varying
Reynolds number on the pressure distribution on a transonic body of
revolution at angles of attack through the transonic speed range. The
effect of a change in sting cone angle on the pressure distributions
and a comparison of experimental incremental pressures with theory is
also included.

The models were tested through a Mach number range from 0.60 to 1.09.
The Reynolds number range based on body length was from 9 x 106 to 59 x 106,
and the cross-flow Reynolds number range based on maximum body diameter
was 1.5 x 105 to 4.53 x 105 for the model at 8 angle of attack.

An increase in Reynolds number from 9 x 106 to 39 x 106 affected
the longitudinal pressure distributions very slightly. These effects
were of such a nature as to cause an increase of 0.05 in the normal-
force coefficient of the body when tested in the subcritical cross-flow
Reynolds number range. This increase is in agreement with theoretical
approximations.

A comparison between experimental and theoretical values of the
incremental pressure coefficient due to angle of attack indicated good
agreement except at angles where separated flow areas existed over the
body.

The effect of a change in sting-cone angle from 5 to g9 on the
pressure distribution of the 120-inch model was negligible up to a
Mach number of 1.05. At this Mach number the effect was to cause a
small increase in the velocity over the rear of the body.


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INTRODUCTION


Long slender bodies of revolution have been used for airships,
fuselages, external stores, and more recently, for missiles. Tests of
these bodies have been greatly accelerated because of their increased
employment as aerodynamic shapes in the transonic and supersonic speed
ranges. Some of the information available for several different bodies
is reported in references 1 to 4. Some effects of Reynolds number on
the pressure-distribution and force characteristics of the RM-1O missile
at supersonic speeds are given in reference 1. Reference 2 presents the
results of an investigation of the effects of cross-flow Reynolds number
on the aerodynamic forces of bodies of different fineness ratio for
various subsonic and supersonic Mach numbers.

Most of the previous investigations of the effects of Reynolds num-
ber on the flow over a body of revolution at high Mach numbers have been
made with zero pitch attitude of the model. The purpose of the present
investigation was to determine the effects of variations in both the
longitudinal and cross-flow Reynolds numbers on the pressure distribu-
tions over a body of revolution at angles of attack from 00 to 150 for
a Mach number range from 0.60 to 1.09. The sting-cone angle was changed
from 50 to 9 in the presence of one body during the investigation, and
the effects of this change on the pressures over the rear of the body
are also discussed. An additional purpose of the investigation was to
present an experimental check of a method shown in reference 5 for the
calculation of the incremental pressure at any point on a slender body
of revolution due to a change in body attitude from zero angle of attack.
Reference 4 presents an experimental check of this method in the trans-
onic Mach number range using a body tested at subcritical cross-flow
Reynolds numbers. This paper presents a supercritical Reynolds number
experimental check of the method.

Three transonic bodies of revolution with identical body profiles
(except where modified for different sting supports) were tested in the
Langley 16-foot transonic tunnel at angles of attack from -20 to 150
over a Mach number range from 0.60 to 1.09.


SYMBOLS


A maximum cross-sectional area, ,R2, sq ft

N
CN normal-force coefficient, -
d body diameter, ft
d body diameter, ft


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2 length, ft

N normal force, lb

p p
P pressure coefficient, q


AP incremental pressure coefficient due to angle of attack

p local static pressure, lb/sq ft

p0 free-stream static pressure, lb/sq ft


q free-stream dynamic pressure, pV2, lb/sq ft

R maximum radius of model, ft

r radius at given station on model, ft

Re free-stream Reynolds number, V based on body length


Rec cross-flow Reynolds number, pV sin ad based on body

diameter

V velocity, ft/sec

x longitudinal distance from nose, ft

a geometric angle of attack, deg

8 meridian angle, measured from bottom of body, deg

p viscosity, slugs/ft-sec

p mass density of air in free stream, slugs/ft3


APPARATUS


Langley 16-foot transonic tunnel.- A description of the Langley
16-foot transonic tunnel giving details of the slotted transonic test
section is presented in reference 6. In this facility the test-section
Mach number can be varied continuously from about 0.2 to 1.09 simply


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by variation of drive power; no discontinuity in operation is experienced
at sonic speed. Figure 1 is a downstream view of the test section of the
Langley 16-foot transonic tunnel showing the 120-inch body installed.

Support strut.- Figure 2 is a sketch of the support configuration
used in the investigation of the 120-inch body. The main support is a
vertical cantilever strut of circular-arc section, capped with a 14-inch-
diameter cylindrical body. The cone-shaped sting is faired into this
cylinder. The angle of attack of the model is varied by rotation of the
complete strut and sting assembly about a point on the longitudinal axis
of the body. Figure 3(a) shows the details of the long and short cones
with included angles of 50 and 90, respectively, and the relative posi-
tion of the 120-inch model to the center of rotation when mounted on
either cone. This center of rotation is 96 inches behind the nose of
the 120-inch body for the long cone and 60 inches behind the nose for
the short cone.

Model dimensions.- The body profile is that of the standard fuse-
lage of basic fineness ratio 12 used in the NACA transonic-wing research
program. One model has a maximum diameter of 10 inches, 60 inches behind
the nose. The rear of this model is faired into a 2-inch-diameter cylin-
drical sting section which reduces the length of the actual body below
the basic length of 120 inches for a body of this diameter and fineness
ratio (see fig. 3(a)). Reference 7, which presents test information
obtained from this identical body at zero pitch attitude, has designated
the model as a 120-inch body. Therefore, for clarity of reference,
despite the above-mentioned sting fairing, this model is designated the
120-inch body. The second model is the same as the 120-inch body with
the exception that it is cut off at 100 inches to provide for a heavier
sting support. A sketch of this model, designated the 100-inch body,
and its sting is shown in figure 5(b). The third model is one-third the
size of the 100-inch body with a 353.5-inch actual or 40-inch basic
length. Figure 5(b) shows the 55.55-inch body-sting combination and its
relative position in the Langley 16-foot transonic tunnel compared with
the 100-inch body. A table of nondimensional ordinates for the basic
body is shown in figure 3(a). The orifice locations for the 120-inch,
the 100-inch, and 33.33-inch bodies are given in figures 3(a) and 3(b),
respectively. The basic length of the body is used to define the orifice
location in each case.

Model construction.- The models are all metal and were maintained
in an aerodynamically clean and smooth condition at all times. The sur-
face ordinates of the 120-inch and the 100-inch bodies were essentially
the same; however, they deviated from the design ordinates as indicated
in figure 4. The maximum deviation was 0.02 inch between 14 and 17 per-
cent of the length behind the nose, and the deviation was less than
0.008 inch from the specified ordinate over the rest of the body.


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NACA RM L55H04 CONFIDENTIAL 5


TESTS


Test conditions.- The Mach number range covered in this investiga-
tion was from 0.60 to 1.09. The test data were obtained at constant
tunnel Mach numbers as the angle of attack was varied from -20 to 15.
For the 120-inch body, the number of meridians at which longitudinal
pressure distributions over the body were obtained was effectively
doubled by rolling the model 22.50 from 0 roll at each test condition.

Figure 5 shows the Reynolds number of these tests. The ranges are
9 x 106 to 11 x 106, 26 x 106 to 33 x 106, and 51 x 106 to 39 x 106 for
the 33.33-inch, 100-inch, and 120-inch bodies, respectively; all based
on body lengths. The cross-flow Reynolds number ranged from 1.5 x 105 to
4.55 x 10 with the models at 80 angle of attack. For angles of attack
above 8, Rec for the 33.55-inch body is in the critical range and
below 80 Rec for the large body approaches the critical region; there-
fore, cross-flow was investigated at only 80 angle of attack. The free-
stream relative humidity was at all times below the saturation point and
generally varied from about 80 percent at the lower speeds to less than
30 percent at the maximum speed.

Instrumentation and accuracy of measurements.- The locations of the
the pressure orifices are shown in figure 5 for the 100-inch, 120-inch,
and 33.33-inch bodies. The pressure orifices in the 120-inch body are
located in 5 meridians of 21 orifices each, distributed longitudinally
as shown. There were 4 orifice meridians on the 100-inch body and
6 orifice meridians on the 33.33-inch body. It should be noted that the
e = 750 and 1050 meridians did not extend the entire length of the
33.33-inch body because of space limitations. The pressure tubes from
these orifices were conducted through the sting and strut, and thence
to multiple-tube manometers. The pressure coefficients are estimated
to be accurate to +0.005. The angles of attack as presented are esti-
mated to be accurate to 0O.1.

Tunnel-wall corrections.- There have been no tunnel-wall corrections
applied to the data presented in this paper. Such corrections exclusive
of reflected disturbances at supersonic speeds are believed to be negli-
gible within the speed range of the investigation (see ref. 7).


RESULTS AND DISCUSSION


Presentation of pressure distributions.- Table I gives the pressure
coefficients on the 120-inch body for 9 meridians and 21 axial positions.
Pressure data on the 33.33-inch body was previously presented in reference 4


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Comparisons of the pressure distributions along the 00 and 1800 meridians
of the bodies are depicted in figure 6 for angles of attack from 00 to 150
and Mach numbers from 0.60 to 1.09 as plots of pressure coefficient against
fraction of body length. The slight discrepancies which occurred at
x/1 = 0.17 are attributed to local surface deviations of 0.025 inch over
the two larger bodies as shown in figure 4. Tunnel boundary reflected
disturbances also affected the distributions over the 120-inch body at the
supersonic Mach numbers greater than 1.02 (no distributions were obtained
over the 100-inch model in this range). These effects were observed at
all angles of attack. A comprehensive investigation of these disturbances
on bodies of revolution at zero angle of attack is included in reference 8.
Reference 7 defines the extent of the effect of these disturbances on the
pressure distributions over the 120-inch body at zero angle of attack in
the Langley 16-foot transonic tunnel. Mild effects of these reflected
interference on the large bodies are noted in the vicinity of x/Z = 0.35
at a Mach number of 1.05. The reflected disturbances become stronger as
the Mach number is increased. At a Mach number of 1.09, the disturbances
cause an abrupt positive increase in the pressure coefficients of the
120-inch body at x/Z = 0.44. These wall-reflected interference appear
to have little or no effect on the pressure distribution over the smaller
33.33-inch body in the Langley 16-foot transonic tunnel at Mach numbers
of 1.05 and greater since the reflected disturbances pass downstream of
the body at these tunnel velocities.

SThe expected pressure-recovery discrepancies between the 33.33-inch
and 100-inch bodies and the 120-inch body are apparent in figure 6. The
3355.-inch and 100-inch bodies show an abrupt pressure recovery behind
x/Z = 0.75, whereas the 120-inch body shows a more gradual recovery
farther downstream on the afterbody.


Effect of Reynolds Number On the Body Pressure Distributions

Longitudinal pressure distributions.- The effect of increasing the
Reynolds number over body sections is to move the transition point from
laminar to turbulent flow toward the nose of the body at subsonic speeds.
This movement would increase the area of turbulent flow over the body
surface and it would be expected that separation would be delayed to
higher angles of attack. Such changes in the flow would be indicated
in both the pressure distributions and force measurements obtained from
the body. However, if a turbulent boundary layer exists over the entire
body, no changes should be expected in the pressure distributions with
increases in Reynolds number (for example, ref. 9).

Comparison of the pressure coefficients at the 00 and 1800 meridians
for the bodies in figure 6 show small differences in the subsonic speed
range. Comparisons at the other meridian stations not included show
similar results. Similar differences are shown in the supersonic speed


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range except in those regions where wall-reflected wave interference
intersect the large bodies. It is estimated that the boundary-layer
flow over the two large bodies was almost completely turbulent since
the Reynolds number was generally about 30 x 10, and reference 10 shows
that transition occurs at a Reynolds number of about 11 x 10 on a
highly polished body. Reference 10 also showed no effect of Reynolds
number at zero angle on the pressure distributions except in a region
of adverse pressure gradient near the model base. Since very small
differences in pressure coefficient occurred near the rearmost orifices
of the 55.55-inch body when compared to the 100-inch body, it is esti-
mated that the boundary-layer flow was turbulent in this region.

Because only slight variations in the pressure distributions along
the body meridians were noted where comparisons were possible, it was
believed that more significant differences might become apparent if the
circumferential pressure coefficients were examined at stations along
the body.

Circumferential pressure distributions.- When a body of revolution
is rotated to an angle of attack, the cross section of the body pre-
sented to that component of the air stream normal to the longitudinal
axis is a circular cylinder. It has long been known that an abrupt
reduction in the pressure drag of cylinders occurs when the boundary
layer changes from laminar to turbulent flow. If Re is below the
critical values, there is laminar flow over the cylinder and separation
of the boundary layer occurs near the maximum radius, however, if Re
is above the critical value, turbulent flow exists and the boundary
layer remains attached to the cylinder until near the rear stagnation
point. Reference 11 shows the critical Reynolds number range for a
cylinder to be from 2 x 105 to 4 x 103. Significant changes in the
pressure distribution around the cylinder should be evident with the
separated laminar flow yielding lower pressure coefficients.

Figure 7 shows the variation of pressure coefficient with meridian
angle at x/Z = 0.10 for all the bodies at 80 angle of attack and Mach
numbers of 0.60, 0.95, 1.00, and 1.02. The data for the 33.55-inch body
from reference 4 are also presented. The x/1 = 0.10 station was chosen
because the local cross-flow Reynolds number for all the bodies would be
below the critical value. There is good agreement between the pressure
coefficients for all the bodies at most meridian angles and Mach numbers.
Figure 8 shows the circumferential pressures for two stations near the
maximum diameter for all bodies at 80 angle of attack and at Mach num-
bers of 1.00 and 1.02. In this case the local cross-flow Reynolds num-
ber is above the critical range for the large bodies and below the
critical range for the 33.33-inch body. The pressure distributions
at x/l = 0.56 and x/Z = 0.61 for a Mach number of 1.00 show that
the small body is developing more negative pressures over the upper


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NACA RM L53H04


surface (8 > 900). At a Mach number of 1.02 and x/1 = 0.56 it appears
that the pressure distributions of the large bodies and the 33.55-inch
body in the Langley 8-foot transonic tunnel are being affected by slight
boundary reflected over-expansions (see ref. 8) since the 55.33-inch body
pressures of the present investigation are more positive at all meridian
angles. At the same Mach number but at the more rearward body location
of x/z = 0.61, the distributions indicate no such interference. The
slotted-tunnel interference investigation of reference 8 made with this
identical 55.55-inch body indicated that no local disagreement in pres-
sure distributions should be anticipated at this body location at a
Mach number of 1.02.

In general, it has been shown that the small changes in the axial
distribution of pressure coefficients may be significant when examined
in the light of the circumferential distributions around the body. Ref-
erence 3 indicated that the normal force of a body might be increased
by an increment of cross-drag and that some differences might be expected
between the forces of a body operated in subcritical and supercritical
Rec. This expected difference in normal-force coefficient could be
attributed to the change in cross-drag coefficient for a circular cyl-
inder from 1.2 to about 0.5 when the critical cross-flow Reynolds number
range was exceeded. Calculation of the normal-force coefficients for
the 55333-inch body and the 100-inch body by the method of reference 3
indicates that an increment of about 0.05 should be evident. The asso-
ciated changes in drag and pitching moment are very small. Figure 9
shows the normal-force coefficient at 80 angle of attack for the 35.33-inch
and 100-inch bodies at Mach numbers from 0.80 to 1.02. The values were
obtained from integration of the pressure data, and the normal-force
coefficients for the 33.33-inch body are from reference 4. The increase
of about 0.05 in the normal-force coefficient of the small body over the
100-inch body which is in good agreement with the theoretical approxima-
tions is estimated to be the result of operating in a subcritical cross-
flow Reynolds number range as shown by the circumferential pressure
distributions in figure 8.

Incremental pressure coefficients due to angle of attack.- The
gradual changes shown in the pressure coefficients even at the high sub-
sonic and transonic Mach numbers encourage the use of a simple approach
to the evaluation of the body-pressure distributions. Reference 5 pre-
sents a method for estimating the theoretical value of incremental pres-
sure coefficients due to angle of attack on an inclined slender body of
revolution. The basic assumption made in the application of this theory
is that the crosswise flow on a slender inclined body of revolution may
be treated simply by considering only the flow perpendicular to the body
longitudinal axis. The variation in incremental pressure coefficients
with the meridian angle for the 120-inch and 33.33-inch bodies at 8
nominal angle of attack and three Mach numbers is shown in figure 10. The
theoretical curve for each case is obtained by the method of reference 5,


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NACA RM L55H04


and the experimental values are shown for the indicated Mach numbers.
The agreement between experimental values and theory is similar to that
reported in reference 4 for the 55.55-inch body alone and these data
substantiate the statements therein that this theoretical approximation
is valid through the transonic speed range for unseparated flow. The
theory of reference 5 was developed for the inviscid case and does not
apply where separation over the body exists. Separation over the upper
rear surface of the body is indicated by a break in the pattern, at a
meridian angle near 900, to an incremental pressure coefficient which
tends toward zero. This can be clearly seen at x/1 = 0.767 in figure 10.

Effect of change in sting-cone angle.- Figure 11 shows the pressure
distribution along the 1800 meridian of the 120-inch body for the 5 and
90 sting-cone angles for 0 angle of attack and Mach numbers of 0.60,
0.95, 1.00, and 1.05. The change in sting-cone angle was coincident
with a change in tunnel axial position of the model as shown in figure 3.
For this reason, the very small axial changes in local velocity in the
empty tunnel must be evaluated in addition to the local velocity changes
on the body attributable to the change in sting-cone angle. The effect
of the change in sting-cone angle from 50 to 90 and the coincident shift
in tunnel axial position is very small. At the subsonic Mach numbers
(0.60 and 0.95) the experimental data showed higher velocities over the
rear portion of the body in the presence of the 50 cone which were fully
explained by the change in axial position. At sonic speed the velocities
were higher in the presence of the 9 cone which was again traced to the
change in axial position. At a Mach number of 1.05, however, the change
in axial position did not entirely explain the higher velocities on the
afterbody in the presence of the 9 cone. The higher velocities in the
presence of the 90 cone are opposite in sense to the difference expected
from a theoretical consideration of the subsonic flow ahead of two dif-
ferent cones. The maximum difference in pressure coefficient is only
0.025 at a Mach number of 1.05, but it serves to emphasize that sting-
support systems should be kept as small as possible with their maximum
diameter far behind the model.


CONCLUSIONS


The investigation of three slender bodies of revolution at angles
of attack from -20 to 150 through a Mach number range of 0.60 to 1.09
has led to the following conclusions:

1. Reynolds number had a small effect on the axial pressure dis-
tributions of these slender bodies of revolution for the range of the
variables investigated.


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NACA RM L53H04


2. The decrease in the body normal-force coefficient when increasing
the cross-flow Reynolds number above the critical range is in agreement
with theoretical approximations.

5. Existing theory for calculation of incremental pressure coeffi-
cients on a slender body of revolution operating at angle of attack
yields results which are in good agreement with experiment except in
areas of separated flow.

4. The effect of a change in sting-cone angle from 50 to 9 and a
coincident change in tunnel axial position on the pressure distribution
was negligible up to a Mach number of 1.05.


Langley Aeronautical Laboratory,
National Advisory Committee for Aeronautics,
Langley Field, Va., August 11, 19535.


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REFERENCES


1. Perkins, Edward W., Gowen, Forrest E., and Jorgensen, Leland H.:
Aerodynamic Characteristics of the NACA RM-10 Research Missile
in the Ames 1- by 3-Foot Supersonic Wind Tunnel No. 2 Pressure
and Force Measurements at Mach Numbers of 1.52 and 1.98. NACA
RM A51G13, 1951.

2. Allen, H. Julian, and Perkins, Edward W.: Characteristics of Flow
Over Inclined Bodies of Revolution. NACA RM A50L07, 1951.

5. Allen, H. Julian: Estimation of the Forces and Moments Acting on
Inclined Bodies of Revolution of High Fineness Ratio. NACA
RM A9I26, 1949.

4. Estabrooks, Bruce B.: An Analysis of the Pressure Distribution
Measured on a Body of Revolution at Transonic Speeds in the
Slotted Test Section of the Langley 8-Foot Transonic Tunnel. NACA
RM L52D21a, 1952.

5. Allen, H. Julian: Pressure Distribution and Some Effects of Viscosity
on Slender Inclined Bodies of Revolution. NACA TN 2044, 1950.

6. Ward, Vernon G., Whitcomb, Charles F., and Pearson, Merwin D.: Air-
Flow and Power Characteristics of the Langley 16-Foot Transonic
Tunnel. NACA RM L52EO1, 1952.

7. Hallissy, Joseph M., Jr.: Pressure Measurements on a Body of Revo-
lution in the Langley 16-Foot Transonic Tunnel and a Comparison
With Free-Fall Data. NACA RM L51L07a, 1952.

8. Ritchie, Virgil S., and Pearson, Albin 0.: Calibration of the
Slotted Test Section of the Langley 8-Foot Transonic Tunnel and
Preliminary Experimental Investigation of Boundary-Reflected
Disturbances. NACA RM L51K14, 1952.

9. Jacobs, Eastman N., and Sherman, Albert: Airfoil Section Charac-
teristics As Affected by Variations of the Reynolds Number. NACA
Rep. 586, 1957.

10. Czarnecki, K. R., and Marte, Jack E.: Skin-Friction Drag and
Boundary-Layer Transition on a Parabolic Body of Revolution
(NACA RM-10) at a Mach Number of 1.6 in the Langley 4- by 4-Foot
Supersonic Pressure Tunnel. NACA RM L52C24, 1952.

11. Stack, John: Compressibility Effects in Aeronautical Engineering.
NACA ACR, Aug. 1941.


C UrFIDE[NTIAL


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TABLE I


PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL


(a) M = 0.60.


a = -2.10 = 4.10

x/Z A B C D E F G0 I x/Z A B C D E F G I

0.017 0.i; .- :r) i,'.,- J ., l ,,, .- i i" ,: :- "'L ':'. l :''" i : :..1: '. ,1) 0776 o.OrI B 0 .071. 9 O ,7&
.0087 .0092 .0164 .165 .0309 .0348 .091 .0531 .. .067 .078 .0713 .0530 .0329 .0146 .0037 -.0018 0 .0018
.100 -.0094 -.0037 .0055 0 .0127 .0128 .0236 .0238 1. 1 .100 .0456 .0530 .0384 .0128 -.0018 -.0164 -.0201 -.0219 -.0219
.133 -.0240 -.0385 -.0309 -.0238 -.0109 -.0037 .0091 .0073 .'.: .133 .0274 .0110 -.0037 -. i10 :- il -.02il .0 .7 -.':, -.035
.. : :8 -..0200 .167 -.0110 -.0116 -.0292 -. .7 o.- -..: .- ... : -. -, -. :- .233 -.0383 -0384 -0475 -0658 079 0749 -0749 -0713 -0713
: ..i. '- ,' .300 -.0420 -.0439 -.: .:I-. -.' -.:.T i .. I -. 'l -.
.. .. .* :. 7 .. .~ .367 -.0460 -.o0457 .: ....:4~ -.:l c -.- -.- -.,,i .
S. -. 546 .33 -.0529 .:Ci 7 .: ..' ..:
... .. I-. -. .- 582 .500-.06021. -.
.. .. -. ... -..546 .567 -.0602 -..: ..-. .. -L-. i-. l -..' ..
.633 -.0567 -.0623 -.0582 -.o660 -.06 -. 655 -. .. .. :T .. .l-7 -..',. ...:.I,
.700 -.0494 -.0531 -.0491 1-.61 -063 691 .. .. -. .0457 -.039
.733 -.0331-.0403 -.0364 -..04 6046. 564 .... .. ..,..; ..-
-.0128 -.0091 -.0202 -.0200 -.0330 -.0309 -.0403 -.0327 -.. -. : -. -.: -.y, ...>6
-.-.0327 .' "I "!., '. :qt'
.0183 .0200 .. -- ; .. 1 '. .: .). .
.032 .0421 .0455 .:- : : ;' .0311 .0255 :- l : c.- .... ..1.. .0457
.632 .0623 .0673 .0605 .- 5 0531 .0527 .0402 .0439 .0493 .0567 .0621 .0621 .6 .. .0640
.900 .0959 .0934 '- .0934 .0982 .0934 .1000 .0934 .0982 .900 .0913 .0932 .0969 .0950 .0950 .0932 .0932 .0914 .0914
.933 .0995 .0934 .0934 .0982 .0953 .10 .0 .0971 .1019 .933 .1077 .1042 1005 .0950 .0932 .0914 .0932 .0932 .0969

a o a = 6.20

: 1170 0.1228 0.1224 0.1283 0.1279 0.1319 0.1334 0.017 0.2165 0.1960 0.1544 0.1209 0.0772 0.0605 0.0441 0.0476 .0441
S <: .:: :I 0841 .0843 0841 .0843 .0859 .0861 .0877 0? .1633 -1539 .1139 .0788 .0404 .0238 .0110 .0165 .0129
0329 .0311 .0329 .0330 .0347 .0366 .0365 '".. .. :'- ..J-,-.. -1 .. .
.100 .0073 .0165 .0183 .0147 .0146 .0092 .0110 .0073 .0073 .100 ..~ ....r .. .... '- .:.18 -....n0
-.0183 -.0092 -.- *r07- '13 -.1037 .133 .V : -
S- -.o 0 .0421 -. .. .- ... *.. "2 ..w .. .. '347 .167 .00 .. .. '*. -. '"-. -'
S 550 -.0548 -.0586 -.0585 -.055 -.0548 -.0550 -.0548 .233 -.0-. : -.
S 550-.058 .0586-.0585-.56-.0548 -.o55 -.0548 .300 -.0.. : -...' : -. :
.367 -.0556 -.0531- -: -. I 9 -.0513 -.0512 .367 -.0401 .. -. -
.433 -.0584 -.0586 -. -. -.r -
.500 -.0621 -.0623 : "- : -, '.. ... -. '). ,*.r -.m -. ,'0
-. '-- .05 .0548 -.0550 -.0548 --- 5. -"''C -. 6*..
"- O -.054 -.05)
i. ,- -. 0623 -06 621 633 -.0771 -.3 .
.700 1. '- ..0623 -.0621 .700 .- -.a c! 3 -. -.0 -
S: 57 -.0458 -.0457 -.0458 .733 -- .4- ..
-.0183 -.0183 -.0183 .0220 .0219-.0202 -. -
S. r .0091 .0 .0uo -.00 .00018 .0183 .0184 .0202 .0202
.833 .0365 .05 4 .0365 .0385 .0384 .0348 :I .0183 .0331 .0403 .036 .0366 .036
.867 .0602o :' .0640 .0605 .0621 .0605 .0621 .06o5 .867 .- .3 .515 .0570 .0586 .0551 .0550 .0515
S .09 .0971 .0987 .0989 .0987 .0989 .0987 .900 .. .0843 .0882 ..* 09 .0919 .0898 .086 .0843 .0827
933 .0 098 .0989 .1005 .099 .0987 .0987 .933 1138 .1099 0992 .0953 .0900 .0898 .09 .71 .101


a = 8.5


- -. 1 1 -

0750 .0420 -.0037 -.0402
. *. ,, -"<. ;-9











.0805 .0622 .0879 .0969
.1299 .1188 .1044 .0987


- 1: : ,
-.0733 -*:,T
-.104 -.1078
- ]I^ 11'..








1*41. .4..:

.0953 .0950
.0953 .0950


-. .
- ui
-.0806






. o3




.0843
. *..t


NACA


COl.TI DEI. IAL


NACA RM L55H04


a = 2.00









NACA RM L53H04


CONFIDENTIAL


TABLE I.- Continued


PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL

(b) M = 0.80.


71' 0
I ,.'.I I



.. .. .. .- I 3 -. -. -. -
-. ... !.' [.. ..:

..... -.. ,n .. -" .-- -33 -.0473 -.0504 -.06 1-. .
..500 -.05- r
-..567 -. -
i .. -. : -. -.. .633 -.0716 -.07oi -.0780 -.0738 -.074- ..
.7c -. -. .- -.06 .683 -.0741 -.0732 -.0791 -.07I .' .
.. .. -. .. .." .. -. -. .035 -.0245 -.0254
.7 -. .. n034 .. 0002 .0002
.3 ..0. 3 l -:I
-~ft L 7. h.-..:- .. -.
.800 .o3 .063 ..0201 .-.9 .0102 .06 .0015 .M .0336 .030
.833 .0527 .0523 .*': .0461 .0443 .0411 .0382 .0325 _- .0528 .0553
.867 .0772 .0758 0761 .0724 .0672 .1 .0634 .. .67 .0551 .0583 .0626 .069 .0724 :' .0736
.900 .1068 .1091 .1091 .1093 .1093 .1103 900 .1062 .109 1103 .1102 1089 .102 .-: .1042
.933 .r "- .1081 .1079 .1056 .1079 .1068 .1116 .1105 .1128 .933 .1208 .1200 .1127 .111 .102 .0 .i02 .1 .- .1090







-7 .0015 .133 .0648 .o03 ..- -. .. ..
-.0317 .167 .0210 .0067 -. .i '- :.- -
.-3 -. -. ,- .233-.0132 -.0219 -. ...- -
-.. -. -. -.0 3 ". ..- -
.- 1 1. .:'- -. l -. ... .
S .. ...... .. ... i -. 0 -. 218


-.0144 -. 00 22 -.0070 --.
-... .. -. -.. .0229 .0271 .
.833 .0431 : ..* .833 **' .053 .0504 .,'
867 0700 .0715 .0675 0691 .0690 .0688 .070 .86 .053 .3 05 0590 .0665 .075 .0602 .0663
.',,95 107, ,,5,, ... ,,,8"
.933 .1091 .1074 1095 .1087 .1083 .1074 1083 .107 .1083 .933 .1342 .1249 1176 1088 .105 .1000 .1066 .1075 .1200

a = 2.0 a = 8.40

0.017 0.1735 0.1779 0. .
.033 .1271 .1310 .
S.0625 -.0706 .: ... : ,
., .0405 .0508 q.. i:, :. .. .
r. ...... 1-u .......... .... ..... ... ... i. .. ..






'. ..' -.0389 -.0343 -.0340 .- 0720 -.042 -.0340 -.0393 -.0242
.. .. -.0120 -0072 -.0071 .767- -
.800 C99 .. 0271 0- .,- I. l
.8w0 .0 .00
.833 .0. '- .. .0516 P *-
.867 .0 .0736 1 .0760 .
.900 110 .1125 .1103 .1113 .1090 .1113 .1090 .u.) .1091 .900 ...: .1061 .103 .102 .099
.933 .1137 1150 1115 .1125 .1090 1 .100 .1078 1100 1091 933 1454 .1384 .1226 .1148 .1092 .1061 .1092 .1111 .1202

INACA


CONFIDENTIAL











CONFIDENTIAL


NACA RM L53H04


TABLE I.- Continued



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF


REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL


(c) M = 0.90.


a -2.5 0


B C D E 1


0.1325 0.1416 0.1527 0.1670 0.1826 0.1986 0.2061 0.2106 0.2336 0.2251 0.2035 0.1953 0.1566 0.1473 0.1282 0.1271 1.1194
.0919 .057 .1017 .1165 .1250 .1405 .185 .1526 .1769 .1750 .1511 .1377 .1052 .0972 .0779 .0802 .0747
.035,i .398 .0429 .0552 .0621 .0760 .0823 .0924 .067 .1007 .107 .0845 674 .O452 .0354 .0245 .0322 .0266
.0173 .0234 .0215 .0300 .0354 .0461 .0 50 .0530 .100 .0734 .0780 .0583 .0407 .0190 .0077 .0021 .0013 -.0061
-.0222 -.215.0062 .006 .0130 .0245 .0269 .0311 .133 .0462 .0322 .0146 .1Ol1 -.0061 -.0104 -.0159 -.0179 -.0192
..o584 I-.0o54 -.0531 -.o66 -.0382 -.0258 -.0190 -.0138 .167 -.0017 -.0072 -.0247 -.0360 -.0552 -.0573 -.0629 -.0573 -.0585
.0702 -.0685 -.0712 .0674 ..o6o6 -.0510 -.0488 -.0423 .233 -.0344 -.0339 -.0487 -.0605 -.0749 -.0744 -.0760 -.0691 -.0716
.0648 -.064i -.0702 -.0663 -.066 -.0532 -.0520 -.0412 .300 -.0399 -.0403 -.0531 -.0637 -.0738 -.0691 -.0683 -.0605 -.0596
-.0584 -.0587 -.0616 .0598 .0590 '? .0455 .367 -.0437 -.0382 -.0509 -. -..0 672 -.0669 -.0640 -.0563 --
-.0670 '.- -.0712 -.0696 -.0680 .0576 .433 -.0497 -.0771 -.0701 -.062 -.0605 -
..0670 ..0734 -.0751 .0734 -.0718 -.0680-.0674 .500 -.0617 .* .5-.0803 -.0744 -.0683 -.0616 1
.0638 -. -.0659 -.0641 ..0620 .567 -.0606 -.0584- .. ..0509 -.0509
S -- -- ..0798 -.0795 -. ': .633 -.0802 -.0765. 'r ***..... -.. ..0595 .0585
-0627 ...0830 -.0849 -.0872 -. .700 -.0911 -.0851 -.0902 -.0893 -.0825 -.0691 -.0618 -.0541 -.0531
-.0414 .0499 -.0587 .0606 -.0652 -.0638 -.0641 .733 -.0828 -.0712 -.0727 -.0669 -.0585 -.0446 -.0367 -.0296 -.0279
-.094 .0158 -.0247 -.0307 -.0357 -.0371 -.0390 .767 -.0464 -.446 -.0432 -.0339 -.0214 -.0094 -.0039 -.0002 .0015
301 .o226 .0158 .0141 0070 .0055 .0037 .800 -.0050 -.0009 .0015 .0077 .0201 .0311 .0321 .0375 .0376
.0567 .0552 .0525 '. .0471 .0420 .0365 .0366 .833 .0288 .0333 .0365 .0428 .0528 .0610 .0594 .0610 .0605
.0823 .0801 .0727 .0749 -13 .0695 .0694 .867 .0603 .0663 .0714 .0791 .0812 .0834 .0801 .0823 .0812
.113 .1154 .1154 1154 .1186 .1175 .1176 .900 .1170 .1185 .1194 .1185 .1162 .1175 .1129 .1143 .1118
.1143 .1121 .1122 .132 .1133 .1154 .1165 .1165 .933 .1279 .1271 .1205 .1175 .1118 .1121 .1107 .1143 .1172


a = -0.10
-- 1


1 -.0211 -










).1637 3
I .1081
.0494
.1i94
* .0194]
.0013
0479
S-.0671
S-.0650
.0618 .
-.0671
1 ..0714 .
3 -.0628 .
3 -.0735
..075

117



' i 11?
E .4ii


.'~ ']


-.-L 47


-.0676
-.06 I






1. 4


= 6.20


I



.. .


S *I.

. .- .. 1 i7 -


" -L J '' l -'*I -


.0883
.0609
.0114-
-.0259 -.


-.0677-.:
-.0853 -.
-.0951 -.:
-.0929 -.
-.1127 -.
-.12? -.
..110 5 -.
-.0809 -.
-.0336 -.
.007 .1
.Omy .(

.1136 .
.101 .


.0 77
982
.



0694 -.1083


1004 -.1182
1154 -.1259
1218 -.1281
1154 -.1138
1293 -.1193
1379 -.1127
1122 -.0787

.
206 .O 477
30666 074
1191
191


Ll J
.'.

..1283 -.1050
..1197 -.0897
-.1133 -0809
-.1133 -.0798
-.1143 '
-.0961
-.0951 -

..0o90 ..0142
.048 -.01
.0206 .0242
.0495 .0466o
.0719 .086
.1137 .1114
.1137 .1147


,,: :





-.0919
-.0769
-.0726
-.0747




.0501
-.244
.0088
-323
.0591
.1073
.1191


- *

4





I






















S0512
.- 1
...,










-.0512
-.0259
-.0094
319


'?
.i09


' NACA


CO;IFI lDEI; IAL


/17 A


.017 0.1315


.0203 -.0190










0.1919 0.192'
.13941 .1444
.0694 .0771
.o42 .5-6
.0201 :

.05143 -.051
-.056 -.0500
-.,36o8 ,"
-.1685
-.065 -.6? 8
-.ol85 -.0788
0-.o871-.08'
.- 2 .:?b



7 1


-- I








NACA RM L53HO4


CONFIDENTIAL


TABLE I.- Continued



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL

(d) M = 0.95.


a = -2.3 a = 4.10

x/Z A B C D E F G H I x/I A B C D E F G H I

0.017 0.1474 0.1449 0.1550 0.1675 0.1877 0.1982 0.2184 0.2198 0.2297 1 ,i ,5.I .'-_ -l' ,.1 **.'. .. 4-h ,:, i :I.. I. '7 .'..1i.r
.033 .1056 .1029 .1141 .1162 .1325 .1388 .1571 .1603 .1703 ? "': l-A 6 ,: i: r :....- ."J4 ,'.*'- 7.'*
.067 .0453 .0424 .0528 .0496 .0661 .0711 .0896 .0875 .0998 .067 .1138 .1080 .0917 .0712 .n-"8 .0415 .0334 .0384 .0365
.100 .0198 .0209 .0323 .0281 .0425 .0414 .0548 .0486 .0599 .100 .0760 .0834 .0672 .0425 ... : .0108 .0057 .0037 .0037
.133 -.0037 -.0201 -.0106 -.0027 .0129 .0168 .0344 .0271 .0374 .133 .0484 .0313 ".I'' *-17 -." -A -.0 -7 -.0157 -.0168
.167 -.0557 -.0652 -.0556 -.0590 -.044 -.0416 -.260 -.0221 -.o106 .167 -.0047 -.0137 .*'- -. '- ,'.i -.:, .. : -.0638 -.0639
.233 -.0751 -.0806 -.0710 -.0806-.0658 -.0683 -.0526 -.0560 -.o454 .:" ... ~ .. -- 3- .0843 -.084 -.0781 -.0782
.300 -o649-.o72 -.0638 -.0775-.0658 -.0672 -.0536 -.0611 -.0444 ., :- .- .: .,3 -.771-.0741-. .0669 -.0659
.367 -.062 -.0621 -.0556 -.0672 -.0566 -.o631 -.0515 -0508 -.0413 .367 -.0418 -.0444 -.0537 -.0638 -.0700 -.0720 -.o680-.0607 -0598
'7 ,- 9 -.7.7 -...:,4 .7 ,-0 -.,-'7i. .-.-U -.o628 -.0693 -.0587 .-433 -.0568 -.o638 -.0731 -.0802 -0844 -.o0781 -.0741 -.0679 -.0659
.:, .,,, -..-..,r ..:c;. ..; -...,71 -..:-.' -.0720 -.0765 -.0669 .500 -.0691 -.0720 -.0793 -.0863 -.0885 -.0832 -.0762 -.0689 -.0670
.=7 .':.. .- .:.'*: -.-*:*. -..:.. -.- :,-: .. ,-.0607 -.0683 -.0597 .567 -.0660 -.0658 -.0721 -.0761 -.0752 -.0679-.0618 -.0566 -.0557
.633 -.0721 -.0795 -.0740 08-.087 -.0802 -.0898 -.0812 -.0898 -.0812 .633 -.0895 -.0904 -.0946 -.0935 -.0905-.822-.074-.0679 -.0680
.700 -.0690 -.0765 -.0720 -.0898 -.0873 -.0980 -.0904 -.1000 -.0914 .'-.. :- .:: -.I- -... ...: ,. -.< -.0639
.733 -.0394 -.0488 -.0444 -.0590 -.566 -.0683 -.0628 -.0703 -.0648 ." -.' -..:,i- .:i .....; .:. .:7W -..k:-: -., -.0332
.767 -.ool6 -.01o9 -.oo65 -.0191 -.0188 -.034 -.0311 -.0396 -.0331 .'C ,' .'.- '. -. -.: .. .0006
.800 .0382 .0312 .0364 .0240 .0252 .0137 .0170 .0076 .0139 .800 -.0027 .0016 .0047 .0129 .0231 .0333 .0354 .0395 .0405
.833 .0668 .0588 .0650 .0558 .0589 .0496 .0528 .0404 .0466 .833 .0341 .0374 .0405 .0497 .0569 .0650 .0641 .0630 .0641
.867 .0913 .0865 .0937 .0824 .0885 .0793 .0834 .0732 .0793 .867 .0668 .0722 .0774 .0834 .0856 .0865 .0856 .0865 .0856
.900 .1250 .1193 .1264 .1203 .1274 .1244 .1305 .1234 .1315 .900 .1230 .1243 .1255 .1243 .1225 1223 .1184 .1192 .1184
.933 .1250 .1173 .1223 .1162 .1233 .1183 .1284 .1214 .1284 .933 .1342 .1305 .1245 .1223 .1173 .1151 .1153 .1202 .1245

a -0.2o a = 6.20

0.017 P.1702 0.1735 0.1771 0.1837 o.1874 0.1909 0.1935 0.1930 0.1935 -.* _: 'T 4. [ ... ..: .11 ,.
.033 .1242 .1284 .1114 .1315 .1340 .1315 .1340 .1356 .1370 : ... ,i. .1, 11 i .:-. ** *.' .. .'."-I ,.I .
.067 .0587 .0629 .0662 .0629 .0662 .0660 .0692 .0721 .0734 .067 .1431 .1296 .0987 .0610 .0313 .0160 .0129 .0190 .0210
.100 .0311 .0383 .0405 .0352 .0384 .0311 .0343 .0311 .0323 .100 .1023 .1030 .0721 .0313 .0057 -.0127 -.0147 -.0127 -.0106
.133 .0065 -.0037 -.0006 .0086 .0117 .0137 .0158 .0096 .0107 .133 .0738 .0487 .0210 .0027 -.0239 -.0311 -.0311 -.0311 -.0290
.167 -.0466 -.0498 -.0468 -.o488 -.0438 -.0447 -.0417 -.0426 -.0397 5 .~ .' .*: -.. ., .- ,j- 7- ..*.-862 -.0782 -.0750
.233 -.071-2 -.692 -.0664 -.0713 -.664 -.0692 -.o653 -.0672 -.o643 -.* ...i .... ... :' ..-.;> -0864 -.0842
.300 -.0651 -.0672 -.0633 -.0703 -.0664 -.0651 -.0633 -.0610 -.0602 ...- -...:i1 -.. -.. **' ..-* -.0710 -.0678
.367 -.0596 -.0590 -.0561 -.0590 -.0571 -. -..=-. .... ...... ...., ..., ,. ... ... -..; -.> ..
.433 -.0691 -.0733-.0715 -.0754 -.0736 -..:.7i -. :.uB -.._. :.? ..,._ .: .1 .-. .....- -...:.-- :.-.:. -..: : :.
.500 -.0753 -.0764 -.0746 -.0795 -.0766 -.0774 -.0756 -.0774 -.0746 .500 -.061 -.0710 .0872 -.104o .:.o .. -....- -.: -.'4
.567 -.0671 -..06 -.643 -.682 -.0653 -.0672 -.0643 -.0672 ..0643 .567 -.0618 -.680 -.0811 -.093. -.l,:: ..;" -....: ...." ...
.633 -.0845 -.0856 -.0828 -.0836 -.0807 -.0846 -.0828 -.0856 -.0838 .633 -.0893 -.0946 -.1056 -.ulo -.1056 -.0885 -.o719-.0690 -.0638
.700 -.0865 -.0866 -.0838 -.0907 -.0890 -.0897 -.0869 -.0918 -.0879 .700 -.1046 -.1069 -.1159 -.1212 -.1077 -.0813 -.0678 -.0639 -.0586
.733 -.0579 -.0610 -.0592 1.0610 -.0592 -.0610 -.0581 -.0600 -.0571 .733 -.0822 -.0905 -.0944 -.0895 -.0709 -.0455 -.0382 -.0352 -.0280
.767 -.0200 -.0231 -.0212 -.0221 -.0212 -.0252 -.0232 -.0262 -.0232 .767 -.0567 -.0608 -.0586 -.0475 -.0219 -.0066 -.0035 -.0035 .0027
.800 .0219 .0219 .0240 .0199 .0220 .0209 .0220 .0209 .0220 .800 -.0128 -.127 -.0086 .0016 .0251 .0324 .0333 0324 .0374
.833 .0546 .0547 .0559 .0516 .0538 .0547 .0569 .0516 .0538 .833 .0239 .0242 .0313 .0436 .0578 0600 .0599 .0538 619
.867 .0833 .0834 .0867 .0823 .0836 .0823 .0857 .0823 .0836 .867 .0565 .0600 .0701 .0805.0834 0825 .0783 .0753 .0772
.900 .1242 .1233 .1247 .1213 .1237 .1243 .1268 .1243 .1268 .900 .1176 .1183 .1253 .1224 .1212 .1204 .1191 .1122 .1130
.933 .1211 .1192 .1206 .1202 .1227 .1192 .1216 .1182 .1206 ,933 .1492 .1419 .1334 .1255 .1222 .1204 .1232 .1296 .1385

S= 2.00 a 8.4

0.017 0.2040 0.2081 0.1962 0.2000 0.1891 0.1805 0.1706 0.1683 0.1645 0.017 0.3208 0.2908 0.2329 0.1759 0.1183 0.0887 0.0804 0.0825 0.0845
.033 .1528 .1601 .1501 .1448 .1338 .1223 .1143 .1151 .1112 .033 .2565 .2323 .1787 .1143 .0651 .0374 .0364 .04 .0446
.067 .0843 .0896 .0805 .0742 .0631 .0609 .0528 .0568 .0528 .067 .1739 .19 019 .0425 -.0004 -.0181 -.0147 -0006 .0027
.100 .0526 .0620 .0549 .0456 .0354 .0282 .0221 .0211 .0180 .100 .1351 .1143 .0712 .0127 -.0260 -.0458 -.0383 -.0294 -.0250
.133 .0270 .0170 .0098 .0180 .0088 .0098 .0047 .0006 -.0014 .133 .1014 .0640 .0180 -.0181 -.0546 -.0622 -.0526 -.0468 -.0424
.167 -.0282 -.0280 -.0363 -.0382 -.0465 -.0474 -.0547 -.0485 -.0506 .167 .0443 .0189 -.0260 -.0766 -.1099 -.1176 -.1068 -.0909 -.0853
.233 -.0589 -.0536 -.0588 -.0638 -.0701 -.0689 -.0731 -.699 -.0731 .233 -.0037 -.0201 -.0608 -.1073 -.1334 -.1320 -.1120 -.0950 -.0894
.300 -.0579 -.0536 -.0598 -.0638 -.o69 -.0638 -.0670 -.0605 -.0629 ;. -. 1. :. -.1145 -.1304 -.1176 -.0935 -.0776 -.0690
.367 -.0513 -.0485 -.0526 -.0556 -.608 597 .0556 0578 -7 -. :..:o -. i -. ,. -.1053 -.1201 -.1115 -.0853 -.070 -.0628
.433 -.O651 -.658-.21 -.06-.o -.0690 .'-.* -. -76 .- ,2 -...5 .-.1238 -.1324 -.1125 -.0843 -.0745 -.0649
.500 -.0743 -.0709 -.0752 -.0750 -.0772 -.071: -... -.:..... ...:71 .,.... -... 7 ..- -.n.j -.1365-.1145 -.0843 -.0786 -.0669
.567 -.0681 -.0628-.0670 -.0648 -.670 -.61 ,-".i -.r .T 0 ::.-...7. ..17 -.ii .' -.. -. r" -
..,"-.,' -. -..,:i ,:7 .. .i ..:, -.0772 -.0730 -.0762 .,. .. ... -.:

7 ( -.,:' l -. -.,.. -.',..'7 -.. -. .'. ,:. : ..:,- .733-.0873 -.1012 -.1140 -.il -..*7 : -.:.A. -.''. ,:0 .* -
.767 -.0344 -.0311 -.0311 029 -.0209 -.0137-.0116 -.0229 209 -.0137.0086 .7 9 -. 5 -0802 -...: ** -. 9 ... 74.. -.-:.
.800 .0096 .0159 .0150 .0200 .0231 .0313 .0313 .0364 .0344 .800 -.0220 -.0252 -.0260 -.11 .0231 .0281 .0272 .0138 .0231
.833 .0444 .0497 .0498 .0548 .0559 .0640 .0641 .0650 06 621 .833 .0167 .0127 .0160 .0363 .0538 .0569 .0538 .0394 .0446
.867 .0761 .0824 .0825 .0855 .0846 .0896 .0887 .0916 .0887 .867 .0494 .0497 .0600 .0794 .0825 .0794 .0763 .0661 .0661
.900 .1252 .1284 .1256 .1274 .1235 .1284 .1256 .1264 .1235 .900 .1157 .1154 .1255 .1266 .1265 1225 .1214 .1174 .0948
.933 .1252 .1274 .1225 .1243 .1215 .1223 .1194 .1223 .1194 .933 .1627 .1513 .1398 .1297 .1255 .1225 .1265 .1318 .1377


CONFIDENTIAL









lb CONFIDENTIAL NACA RM L53H04



TABLE I.- Continued



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL


(e) M = 0.99.



a = -2.05 a = 4.10

x/l A B C D E F G B I x/l A B C D E F G H I

0.017 0.1657 0.1612 0.1662 0.1808 0.1936 0.2112 0.2240 0.2367 0.2387 ; I :1 ** .- ** : ; :. '- ,. ,..:: ,.' I :3
.033 .1178 .1211 .1241 .1338 .1437 .1563 .1672 .1789 .1789 3 i.-. ,':: r .* 11*'., ''.: :" ':-3
.067 .0524 .0574 .0604 .0662 .0731 .0878 .0976 .1064 .1064 ...* ; i. i' 1063 .0838 .0642 .0515 .0446 .0495 .0485
.100 .0231 .0339 .0339 .0378 .0447 .0515 .0604 .100 .0846 .OtB7 .0750 .0525 .0358 .0202 .0143 .0123 .0133
.133 -.0004 -.0092 -.0092 .0084 .0143 .0300 .0378 .', -' .133 .0553 .0388 .0250 .0221 .0055 -.0004 -.0043 -.0102 -.0102
S.- ;! ,- .I. .i *. .167 -.0111 -.0190 -.0317 -.0493 -.0659 -.0767 -.0816 -.0787 -.0777
: ': -" "' ': i .. .- : : ." ''.: .'' :' -.0953 -.1012 -.1012 -.0983 -.0963
I.. .. II : -. ..:' : .9 .".. 2-.1070 -.1051-.1022 -.1002 -.0982
S. : ..- ,. .367 -.0319 -.0376 -.0464 -.0572 -.0640 -.0689 -.0659 -.0620 -.0591
.. '': :.'"- '": ;! .i- ... .433 -.0571 -.0660 -.0738-.86-.0875 -.0855 -.0796 -.0767 -0738
S ..; : .- -.0051 .500 -.0620 -.0650 -.0708 -.0816 -.0855 -.0846 -.0767 -.0718 -.0689
.' :, ,;- ; .... ..,: .'.';:. .5 -.0915 .567 -.0962 630963 -.0992-.1051 -.1002 -.0943 -.0816 -.0806 -.748
..0993 -.1043.1042 -.1062,062 -.1072 .633 -.1098 -.1051 -.1100 -.1100 -.1090 -.1022 -.0924 -.0914 -.0885
,"- '- -.1052 -.1141 -.1130 -.117 ..l.1i- \- .700 -.1303 -.181286 -.1286 -.. 1. .1. -. -982 -.09 0914
S- **'" '.,'. ". I- *" -,.0699-. ..:. ,,--: .733-.0991 -.1032 -.0953 -.. -. -.- L -.0464 -.o425 -.0395
S. ', -.0200 -. : -. -.:.* .767 -.0326 -.0376 -.0346 -.0258 -.0141 -.0043 .0025 .0045 .0065
S ... .0310 .0241 .0221 .0202 .800 .0094 .0114 .0153 .0211 .0329 .0427 .0466 .0476 .0505
.833 .0739 .0750 .0721 .0701 .0672 .0613 .0564 .0535 .833 .0455 .0476 .0524 .0583 .0681 .0740 .0759 .0720 .0750
.867 .0983 .1025 .1005 .0995 .0966 .0976 .0917 .0897 .0878 .867 .0797 .0818 .0877 .0936 .0975 .0975 .0975 .0965 .0975
.900 .1335 .1358 .1348 .1358 .1358 .1407 .1397 .1407 .1388 .900 .1354 .1347 .1376 .1347 .1337 .1327 .1297 .1288 .1297
.933 .1325 .1319 .1280 .1299 .1299 .1328 .1339 .1358 .1348 .933 .1442 .1405 .1366 .1307 .1278 .1249 .1258 .1268 '1337

a = -0.2 a = 6.20


0 1, .. .-- I.K .. ,:, I' :' : .-... ,* '- 0.017 0.2949 0.2810 0.2474 0.2163 0.1759 0. I". ~I i : .
i 77 \i- .-u1- is s1- i .i .--.. t0: > .033 .2323 .2251 .1945 .1555 .1210 .,. "':? .... : .. .
.067 .0672 .0761 .0751 .0761 .0771 .0829 .0820 .0888 .0869 .067 .1502 .1427 .1161 .0741 .0456 .0251 .0231 .0280 .0319
.100 .0368 .0486 .0487 .0476 .0467 .0476 .0457 .0486 .0467 .100 .1091 .1084 .0838 .0437 .0172 -.0063 -.0053 -.0063 -.0014
.133 .0123 .0045 .0035 .0182 .0182 .0251 .0241 .0222 .0212 .133 .0798 .0565 .0319 .0124 -.0121 -.0249 -.0229 -.0269 -.0210
.167 -.0562 -.0553 -.0553 -.0524 -.0524 -.0494 -.0494 -.0416 -.0436 .167 .0153 .0006 -.0229 -.0573 -.0826 -.1004 -.0993 -.0955 -.0895
.' .. P 137 -. *. .233 -.0376 -.0416 -.0601 -.0935 -.1110 -.1210 -.1130 -.1073 -.1013
S, .. ... ...... ... 55 -. I ....:," '.' ".' .300 -.0512 -.o612 -.0787 -.1122 -.1238 -.1229 -.1101 -.1043 -.0973
.367 -.0560 -.0524-.0534 -.0533-.0553 -.0543 -.0563 -.0504 .0524 .7 0..11 ..-7 IL-.07.. -.0836 -.o886 -.0768 -.0690 -.0611
.433 -.0729-.0759-.0759-.0759-.0769-.0720-.0730 -.0720 -.0740 .: .. .-.1061 -.1033 -.0866 .0808-.0729
S...... -.0720 -.0740-.0700 -.0720 .. .... .: -.. -.1042 -.1033-.0836 -.0759 -.0680
....- .,- .. .. ~ -.0808 -.0799 -.0837 -.0838 .567 -.0933 -.0975 -. 1 .107 -.-11L .1053 -.0758 -.0788 -.O640
.. ,.: .- ,!I 1 -. I. i 1. ,i. i4 -.1014 -.1034 -.1053 -.i :- .633 -.1080 -.1082 -.1199 -. .:'~ :: .-.113' -..* -. -: '
.700 -.1082 -.1033 -.1054 -.1073 -.1093 -.1073 -.1093 -.1112 -.ii.- .700 -.131L i -. 1 '* -.1.1: .-. .-.'::
.733 -.0611 -.0602 -.0622-.0622-.0642-.0622 .):. -...... -..... .733 -.1070 i. 7 1-.. .... .-' -.0307
.-'- -- -.0131 -.0151 -.0131 -.0151 -.0151 ..: -."Ti .767 -.0451 .i. ....' ....... .... ..:...: :- -.. :- .0065
:83 ...." .0339 .0329 .0310 .0349 .0320 .0339 .0320 .800 -.002 :. .,, .'" .. .** ... ,1 .047,
.833 .. ... .0663 .0663 .064 .0692 .0673 .0653 .0634 .833 .0351 ... .,.,:. .'. .0691
.867 .* .. .0967 .0967 .0948 .0967 .0957 ."- .0948 .867 .0671 .0673 .0789 .0878 .0946 .0918 .0917 .0829 .0877
.900 .1358 7 .' .1369 .1359 .1350 .1388 .1369 ':- .1369 .900 .1297 .1271 .1357 .1310 .1328 .1300 .1298 .1202 .1240
.933 .1309 .1320 .1301 .1329 .1320 .1329 .1320 .1310 .1301 .933 .1600 .1516 .1465 .1359 .1338 .1290 .1347 .1339 .1485

S= 2.00 a = 8.4

0.017 0.2253 0.2192 0.2119 0.2094 0.1973 0.1898 0.1816 0.1810 0.1796 0.017 0.34160.3177 0.2609 0.2120 0.0lL..- .I'- .' .': 0.1033
.033 .1696 .1722 .1659 .1594 .1493 .1369 .1297 .1300 .1?7A .033 .2732 .2590 .2070 .1493 ..''- .'' ':L ':-- .0661
.067 .0934 .0976 .0926 .0829 .0750 .0712 66 .0682 .067 .1853 .1719 .1249 .0642 .0172 -.0023 -.0004 .0133 .0172
.100 .0602 .0682 .0632 .0525 .0456 .0369 .0319 .0290 ** .100 .1442 .1356 i.' :,, ,:, .',,'..- .. ,:,.
.133 .0338 .0222 .0162 .0241 .01 1 *:' *** .133 .1130 .0818 .. ;' ."',r .,.." .: .- :. ,
.. .. .' '. ,.L," -. l ..' ... I "..., .167 .0485 .0280 --..1- 1 -..:" .. *'r -. L .'. .r''t-':
; .. ..- .. .- -.0571 -.1061 -.1344 -.1413 -.1247 -.1080 -.1022
S ... -.0943 -.0975 -.0963 ~ .'' -, -.0748 -... -.:. 1.-.: ... ',-: -
S *. '. -. .: .. -.0581 -.0573 -.075 2 8 *,i : .i. l .. : :-
.' r. ,,,. .. ,:- ': ,-. ,- -.0748 --0759 -.0738 .' '-. '"-' -, ,:, : I'"' -.' .

.567 -.0971 -.0847 .0924 -.0837 -.09 ; .. ... -.1 ..- .. : -.;7...' -.'.: -.,
.633 -.1079 -.1073 -.1031 -.1053 -.0992 -.1014 -.0943 -.0994 -.0943 .. -. .. ". i *' -,:- -'.. 'I'.
.700-.1264 ..1112 -.1207 -.1122 -.1178 -.10,. .- .:'. :- 1080 .700 -.1274-.1335 -.1481-.' -. '.': :-! -. -.: -.;'
-.0690 -.0659 -.05' -- '503 .733 -.1186 -.1354 -.1354 -: T :. ..VI0. I' -. -. I .
S. .. -.0190 -.0121 -.0102 -.0053 -.0043 -.0023 .767 -.0512 -..')l1 3 ?1 l- -. ,-. 0 -...i -.o,:.
.800 .0221 .0241 .0270 .0280 .0329 .0388 .0427 .0447 .0456 .800 -.0063 -. :-', ,, ':' .' -:. .
.833 .0573 .0584 .0603 .0633 .0671 .0722 .0750 .0722 .0740 .833 .0328 ,' .'* .:. .
.867 .0895 '." ... 0947 .. .1004 .0996 .1004 .867 .0641 ., ..... "
.900 .' .1369 .. ** .1366 .1349 .1356 .900 .1325 .1317 .1415 .1425 .1434 .115 .139 .1337 .1297
.933 '- .1349 .1337 .1329 .13.1301300 .1297 .129.129 1297 .933 .1794 .1709 .1571 .1464 .1425 .1405 .1415 .1454 .1542


C NFIDENTIAL







NACA RM L55H04


CONFIDENTIAL


TABLE I.- Continued


PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL

(f) M = 1.0.


S-2. a 4.10

x/l A B 0 C 0 E G H I x/l A IB C D E F 0 H I

S317 .1 17.5 016.. I 68 .: 1931 C 1r7i 10 3 -7 -.I -. :L57 :>.6;':C 0.017 0.2667 0.2567 0.2401 0.2206 0.2013 0.1757 0.1645 O.1610 0.i6o6
.033 i156 ..."86 12' l' I? I.5I ..676 .'i7 i,;i ij, .033 .2067 .2050 .1907 .1669 .1470 .1258 .1179 .1102 .1121
.067 .0593 o,;] .*91 .- Y. 2 .0 -6 .: 73 : 1 .1110 .1:.90 .067 .1273 .1268 .1131 .0907 .0714 .0555 .0529 .0535 .0568
.100 .0125 .0379 .0350 .0398 .0428 ..4.i. ?7.6 .:? '.4 *-7. .100 .0886 .0955 .0811 .0574 .0423 .0242 .0209 .0164 .0190
.133 .0057 -.OOt0 ..oo80 *:l. j ,) .'1'17 :,':; ~ :, 118 .0408 .133 .0625 .047 .0326 .0262 .0132 .0086 .0025 -.0051 -.0023
.167 -.0704 -.0802 ..0842 -.3 656 A71. : I 17 .- o56-.0266 167 -.0081 -.0295 -.0285 -050 -.0605 -.959 -.0751-.0764 -.0721
.233 09:9 '89 e -.;:.61- .:'; -..:.0" .619 ..'.53,. '..6 .,33 3- 9. 99 ->.13 -.;r 087 .~ ..:7:6 ^8" 6 8 81.8
.30 -.01968 .0..8 ..10 r. :.0* ?. 8 .3 :. .:': ."~ 8; .."8 .- 8 : ... .- .- .o -9
33 .603 .3 -0 l .69. .6. 6 C : :',- ; ,"L* -c.. c':' 5 '770 ..--. .07 7 .1 -.070 .065 644
.8:-. ...c' .08.. :. .: 8-. .61. 0 .729 72-. 1 8- :6(.)- .75. .. .33 9 2.8 8.: :7608 :' -.0692
.567 -.038 1 .:7; ..:803 ..10 0. *6- ..098 :93 1:.:8 : .:9. ..:.- 1::. :995 :.i-86 :65 -.0770
.633 ..C9-' .. 7 1 "i;- :3 1- 1.i i :5 .&i ...C65 .33 .. .. t 1;9l 00 .:LI 1:- : -.0906
.70.:.0 l 11.6 :9': 04'. W' 6 1l4 .'.' .. 0 2-\ :.'. ;- 126? 5. -: ?97 3*3
.733 -.0773 -.0909 '2: ..:4i .077 -.1251 -.1292 -.1329 -.1311 .733 .1339 -.13 99 -.1362 i 1 -...11 -. :?3) .:7't:. L- :.
.767 .0105 .0047 .0018 .0002 -.0061 -.0119 .0139 -.0226 -.0158 7.7 1-8 -2-7 4 01. -. 11 -. .0057 .0112 .0115 .0142
.62 .o544h .0593 .0506 .0544 .0408 .0466 .o140 .0398 .0291 : .: :'.7 8 :3:V C.'l .0545 .0568 .0594 .0617
.833 .0827 .0857 .0780 .0827 .072) .0769 .0653 .0652 .0565 816 ..:*, 7 59. :'E 3f 9; '8- .0838 .0859 .0809 .0850
.867 .1061 .1101 .1034 .1081 .1014 .1062 .0965 .0993 .0916 B6' .5O *907 .:b .:I".. .1073 .1063 .1043 .1063
.900 .1403 .1432 .1176 .1442 .1395 .1481 .1424 .1472 .1415 .900 .1438 :.L. .1451 1424 .1422 .1395 .1393 .1356 .1383
.933 .1383 .1384 .1307 .1335 .1268 .1393 .1366 .1423 1376 .933 .1515 .- .141 .1297 .1354 1317 .1325 .1346 .1,12

a. -0.20 a 6.20

*.017 1609 0.1 0.1901 0TG 0.2077 0 21368 ?21L. e; i1 -:' 0.017 0.3Ci : i2 :;9 .' :* 8 .&,9 I1.7i : 1t 5 13)'" ).Lj5
.03) .1)372 153 .,L7 .I 5.2 1579 16.L 1677 1., 173i .033 .2M9X 73. i i .6"; .2". .:.986 :9..6 .0.:.7 C9g8
.'I7 .687 c .5799 .1769 076: 769 1839 .:. .067 .15'.. .9 ..*9 .Ai:' .3 :':97 ..9 e .7)l
.10) .c .056 5 i :6 :5 :5 5 4'.' .L :..,': 2 Y: 1 .o100 .1148 .1169 .0879 .o496 .0219 .0008 -.004 -.0002 .0035
.133 .0161. .0.66 ..219. '21. .: )3.. .:I63 IMl ..j '6 .133 7 3j -.;37 j7L 0.:72 -r :.6 1781 0187 0i-9
.167 !.096 ..i 76 1..675 -.. :. .;- .167 .:.'.. .: *7 69 l- l .: :: -
.233 -.0859 -.374l." -... ".1:735 :71. ': 7:. *:'c :'7 '197 .233 -..323 173 56' : 81 171 .- 1.5 -.1061 -.0949 -.0915
.300 -.091 8 -.,;i, -.090'3 -.',W ':.. 6 .:.< .': :9.* '1,38 ..",9; 3 -.:"' :-'M 8.) .3 9 '.' :158 -.1j, -3 .:.
.167 -.054. -.0'5 9 .A-o. .1 8 ..:.*88 .D .70 59 1. sia .s 7 :'2-51 3".< -.5.Be N0:' ; :''80t ? 0:39 .:,8)9 -.:'31 -.'.L .
4*33 ..O65 076- .7 7'85 : *: "- 5 2;7 *l. '7> .*r-j ii -..:: ",.: .- :<9 8't '0974 r:.: 6-07: -.36*5 ':634
.500 -.B75 .0676. 9 :-5 :l 1..48 -?' .- ;-. "- 18 ..071. 1 :07 --. I -i 8 :18 5 371'" -.6
.567 -.3859 -.085" .03822 ...;91 '930 -.93, .:... ..*9. ..j*2 5' -..91. ..j91IC 1:5 ..25l .1l 7 ..0% OB" ..-4- '-
.633 -.1035 1.077 -.1027 -..10" 1037 17-8 1o,7 -l8 7 10-' .633 -.1126 -.1203 -. 15 3 -.1326 -.: Y .8 Y73 8 .63 ,099 I :.6
.700 -.1093 ..1.7,- 6 -.12.i33 11L.1. .191 1105 -.1233 -.1134 .700 -.1339 -.1388 -..-:-9 L'::3 164l9 l.2 ..-? I ..2 C L0993
.733 -. 957 -.10' :. 97 114 ,07 ..113. ..1..5 -.1116 -.1085 '3 ?') .' -..591. ..i.i37 -.235 -.:871 ..0731 ..i.oc6 .56t
.767 .02l ..l\ ..lB.. l-.CLi : ".;2; ..'.' :; [, -0.0051 -.0021 .7'" '*"5 -.':.:9 : 1-.. ** il :..: .:l :7l 02 :
.800 .05,:5 '51. .:'. .).77 .,'.67 087 :4':' .0487 .0457 .800 .0190 .0203 .0200 .0301 2.7. :.,i.5 -5;1 *?3 5,88
.833 .0797 .0799 .0808 .0790 .0769 .0790 .0759 .0751 .0711 .833 .0o8o .0496 .0520 .0652 .0762 .0818 .0791 .0711 .0791
.867 .270 .1073 .1130 .1063 .10 .1063 .10652 .1044 .1033 .867 .0780 .0789 .0879 .i004 .1024 .1033 .0985 .0935 .0956
.900 .:;6 .1454 .1462 .1454 1L6 .1474 .1482 I51 .1472 .900 .1380 .1394 .1431 .1423 .1393 .1404 .1373 .1306 .1305
.933 .1411 .1386 .1394 .1337 .1345 .1396 .1413 13 .1403 .933 .1680 .1609 .1538 .1345 .1412 .1404 .1412 .1462 .1577

S- 2.0 a 8.0

0'.17 .1? 9 0 :?i j.2219 ?.)0f.6 : ':( 19'2 16 98: I:.18961" .6t1 0.017 0.3170 0.3225 0.2680 0.2104 0.1547 L:* li9 0 133i 0 1'1 1 i ll:1
.033 l 81 77 7 '? .. l650 668 l481 84 .7i .3.-L .033 .--'8 .2660 .2128 .1500 .1014 ,:C7,1.. '. .; C 7:i.
.067 .1042 .1034 .1015 .0907 .0831 .0731 .0734 .0721 .0685 .067 .1863 .1763 1304 .0632 .0238 .o.00 a :05 L ". :?.8
.100 .0684 .0751 .0705 .0604 .0520 .0418 .0384 .0340 .0316 .100 .1467 .1412 .0936 .0359 -.0052 -.0265 ..-f? L 01.29 -.o0
.133 0432 0272 0219 .0281 .0l8 .0?.' 0190 .0115 07.l .133 .1167 .0866 .0u13 -..o:8. '. :.ji 3 in -.:i;31 : .1. ;':
.00167 .3 ..C0L;: ..1. ..07 0.0.B .0 9. .:0 7 1. 1 '5 I.0" 1.99 01:8 9 .0 .04. .0 i:- 8 j1 ;1. _.0996 -.09i'
.)3i j 33 .:.27 -..,o-.o.'. -:.7i .0 5 :.7- 1**3'i -.5: 3.. 0:'. 0C1 L7 1. ii l95 -.1215 -.0996 -.0953
.$*-. 4 .17 ...< 3818 ..8.9T.8 -" 070? .^79 7.y;* ijA7 v.^ .:. *j'P **.9 V 4860 1I.B ;*<* 1-6 8- 12?,1 10;i. I-AE
. 197 L3 O M -.. 0" 13`A .0Jl* Ll -)rIl : .0 7: j)i3L
.500 -. 8 .686 63 62 37j .081. 2 .7 .' 7" 1 .: -0 3.3 .: 3 D' *:i .-8 .1L ':. 4..i..7; .0857 -.0792 -.0653
.67 -.0911. -.0672 .- 887 -.094.0 ..0387 .. \ B ,1 .0 108 .- 13 .567 1--' .0 796 ,0' 101 .08 :.5` '9:.5 9V1' 0-7
.653 108 -..111 115? 1077 l .13 7. *?7 .1. i3. 1.66 .,.. 36.:. D:.-; )W .1t" -. ..6" -. 9
.700 -.1205 -.1155 -.1159 -.11. 11' *.M 0i 7 ;:61 -.1077 -.1071 .70:. -.133 .': ;1" .7.- i. l 8 l.:4 :;
.733 -.1176 -.1233 -.1159 -..117,. o08: ..- 29. ; 68-."8'2 cfr .. 8. 5.' ,: '.l'- .L ;. 1; :. 1.
.767 -.0062 -.0100 -.0072 -.0051 .0006 .0018 .0045 :,08$ 1:>83 7r' 1:'6 -. 789 -.1:: '4'*3 .:- :. :7.: :. -'
.800 .0364 .0389 .0413 .0418 .0462 .0516 .0540 .-:6*S :*578 .800 .0161 .0125 .0093 .0213 .0471 .-534 '' ('L* -7
.833 .0684 .0692 .0714 .0731 .0782 .0819 .0850 .0819 .0840 .833 .0441 .0437 .0432 .0632 .0771 .e17 -*7 :; :. .%* I
.867 .0994 .1005 .1035 .1034 .1054 .1083 .1093 .1083 .1093 .867 .0722 .0739 .0820 .1041 .0859 1:0. 29.1. 086rw c0-
.900 .i78 .i464 .1471 .1444 .1452 .145l .1452 .1 .35 .1442 .900 .1409 .1422 .1,79 .1529 .1 .1500 .1469 22 .1362
.933 .1449 .115 .1413 .1327 .1394 .1376 .1374 .i 36 .1384 .933 .1844 .1773 .1643 .1402 .1479 .1490 .1469 .1568 .1614


CONFIDENTIAL









CONFIDENTIAL


NACA RM L55H04


TABLE I.- Continued



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL


(g) M = 1.01.


S= -2.35 a. = 4.10

x/l A B C D E F G B I x/I A B C D E F G H I

0.017 0.1780 0.1721 0. :- -'' ..' *'. '. ;30 0.2510 0.2575 0.017 '. -.1 'L "3'.. : :' l1o. 0.1891 0.1651 0.1716 0.1651
.033 .1337 .1293 .:':' L .'' 51 .1867 .1967 .033 *'7: ." ..' I.n .iL..' .1279 .1187 .1182 .1148
.067 .0672 .0631 -^ .0718 .0886 .0933 .1118 .1166 .1224 .067 .1291 .1299 .1109 .0930 .0713 .0639 .0539 .0629 .0597
.100 .0361 .0387 -.'' .046 .0606 .0602 .0770 .0680 .0770 .100 .0866 .1007 .0810 .0609 .0385 .0289 .0211 .0221 .0191
.133 .0152 -.0021 .0056 .0154 .0297 .0349 .0539 .0465 .0539 .133 .0625 .0493 .0307 .0309 .0133 .0105 .0037 .0037 -.0002
.167 -.0580 -.0683 -.0581 ..0606 -0446 -.0411 -. -~. -- -. .167 -.0069 -.0118 -.0302 -.0429 -.0620 -..'': -..-. -.',2 -.0688
.233 -.0753 -.0820 -.0735 -.0820 -.0697 -.0703 -. -. '.;' *"- .233 -.0504 -.0468-.0630 -.0740 -.0891 -- 1'..l, -.'jll -.0852
.` : ~ .. ,- .; -. -.0813 -.0781 -.0735 .-.04 ..... .,, 'i .. i.. -..:.l: -..:7 -.0943 .0978
., -..- 7 -.0600 -.0586 -.0504 .-- -.' -.. -.: -.0710 -.0746
.433-.0724 -.0859 -.0784 -0907 -.0813 -.0839 -.0706 -.0761 -.0677 .433 -.0697 -.0720 -.0862 -.0895 .-.0 0895 -.0910 -.0798-.0852
.500 -.0580 -.0693 -.O620 -.0742 -.0658 -.0722 -.0600 ..;:- .500 -.0648 -.0594 -.7i; :T*.L- -*:. i: *. .:7r -..L: 3-.,*r
.567 -.0647 -.0732 -.0677 -.0800 -.0735 -.0810 -.0697 :7T -- -.0720 -.' -.. i ...:. -
.633 -.0859 -.0937 -.0909-.0995 -.0957 -.1044-.0967 -.1034 -.0967 :' -.1021 -.i... :I -..:** -.:. .,: -.6.2
.700 -00 -.1160-.1121 -.1267 -.1237 -.1306 -.1218 -.1287 -.1218 -. -.:I 1 1 :; 11.- I -..:- -.:r -
.733 -.1061 -.1190 -.1160 -.1287 -.1295 -.1443 -.1392 -.1482 -.1411 .-: -.1526 -. i- 1467 -.1374 -.1186 -.1142 -.1021 -.1046
-.0330 -.0528 -.0581 -.0907 -.0890 -.1 1 1546 -.1399 -.1394 -.0982 -.0814 -.0439 -.0446 -.0293 -.0369
SA. .. h .0590 .25 38 -. .. .- .800 .0345 .0415 .0385 .0483 .0501 .0600 .0559 .0619 .0588
.833 .0980 .0913 ,'.' .0925 '. .0757 .0828 .833 .0702 .0755 .0771 .0852 .0887 .0969 .0935 .0949 .0926
.867 .1211 .1166 .1224 .1127 .1194 .1108 .1146 .1059 .1118 .867 .0982 .1066 .1080 .1143 .1138 .1163 .1138 .1163 .1148
.900 .1520 .1458 .1533 .1468 .1542 .1517 .1581 .1517 .1571 .900 .1484 .1531 .1506 .1502 .1457 .i'- .1428 .1454 .1428
.933 .1491 .1400 .144 .1390 .1407 .1410 .1504 .1439 .1504 .933 .1542 .1541 .1457 .1454 .1322 .1' .1370 .1434 .1457

a. =-0.20 a 6.20

0.017 0.2006 0.2059 0.1989 ."=. l. o. ; ..^P i .. .: ,*:. l.. : : 0.2223 0.1771 0.1582 0.1434 0.1426 0.1434
.033 .1514 .1 ). .'~~ .1 1..i -';: -I -:C: .1621 .1279 .1057 .0981 .0931 .0990
.067 .0799 .:i'' ..7 .0873 .0907 .0912 .0945 .0999 .0994 1671 .1504 .1241 .0834 .0566 .0377 .0374 .0416 .0451
.100 .0481 .05811 .0578 .0562 .0559 .0513 .0568 .0523 .0578 .100 .1219 .1193 .0913 .0494 .0239 .0027 .0066 .0027 .0094
.-..- ~7 ..-..L' .0365 .0319 .0327 .1 .0969 .' .'-..3 .0192- : :' ..:I -..,'Y I*0 E
-.' .. .. ... .:i .- ."' 1. .0267 i- 3. 7- -..05.2 l. : '. :
r ; ...-....- I- .... .. .233-.0252 -.0361 -.0570 -.0896 -.1033-.1110 -.0994 -.0925 -.0869
... ... .. .. .300 -.05 -.0682 -.o869 -.1207 -.1293 -.1275 -.1110 -.1022 -.0946

.. ... ..r. .-.0785 -.0741 -.0775 .41 -. -. *L -. -' 1 ..- ,.7" .. --..
.500 -.0639 -.0643 -.0601 -.06631-.0659 -.0653 -.0640 -.0624 -.0630 -. r... .. -...:., ...:i- -..:.7 -...r.: -.':.
: ,. .-.0717 -.0702-.0698 -.0702 -.0717 .567-.0646-.0760-.0850-. :. -.I. : ,:. -.:. *r. -
..:. ... ...-:--.0939 -.'*. ... ..- 0.. .633 -.0963 -.1061 6-.168 -. ; -.1 d r.i..: -.. r, ..j- -.0,:
.. -.i .- .. ... -.1?- .i' -.. *.. ."' .700-.1223 -.1306 -.1370-.1508 -.136 -.1207 -.1052-.1071-.0956
.;6 ..... '' ... 1314 -.1326 -.1334 -.1326 .733 -.1492 -.164 -.1669 -.1644 -.1380 -1187 -.1013 -.1003 -.0898
.767 -.0610 -.0663 -.0640 -.0663 -.0659 -.0663 -.0698 .. .. .767 -.1675 -.1731 -.1592 -.1265 -.0705 -.0449 -.0329 -.0342 -.0224
.800 .0539 .0552 .0549 .0542 .0539 .0552 .- : : .800 -. .0299 .0364 .0396 .0566 .0523 .0557 .0503 .0624
.0905 .0912 .0907 .0892 .0887 .0931 .' : .8-: .*' .0649 .0721 .0795 .0904 .0892 .0923 .0824 3
S.1156 .1184 .1177 .1164 .1158 .1164 .1158 .0940 .0941 .1067 .1106 .1145 .1106 .llq6 .1038 .8i>~
.900 .1524 .1525 .i .1545 .900 .1498 .1465 .1549 .1475 .1501 .1465 .1472 .1378 .14'.
.933 .I1. .' .'- .1466 .1371 .+-' .1448 i. .933 .1786 .1679 .1607 .1524 .1443 .1465 .1530 .1562 .1674

a = 2.00 a 8.40

0.017 0. .:** ..- 0.2093 0.2098 0.1948 0.1961 0 i 1 3 .' : *:. ".. .. L.. i..i .
.033 *. .1610 .1475 .1437 2' :-ir .. .071. .077'
.067 .108 .1077 .1031 .M'. .0867 .0795 .0761 1998 .1763 .1288 .0,'"' : .0. .. .. I .*.
.100 .0701 .0776 .0722 .- 0529 .0435 .0413 .0348 ., I 1517 .1366 .0941 .0 -.0' 'i, ..' > -.C>( L
.0319 .0278 .0329 .0278 .0251 .0220 .0154 .0182 .133 .1248 .0871 .0412 .I .1 = -'> -. .- l"' -. 010
., ... .. .- .. ... i. .167 .0575 .0328 -.0127 -. : l- i*- rll I1 -i .
.233 --* -. -- .233 -.0040 -.0215 -.0599 1 -. ,- .' I,- '-' -. -..

.433 -.073. -.078C I : -.433 -.0386 -.0613 -.0926-. .': -.L.i -~ -.'' *. -. .
.500 -.0657- .-. I ,.' .-.i. .500 -.0454 -.0613 -.0888 -.1166 -.1196 -.1059 -0753 -.0729 -.0580

.700 -.1197 ,- .i ..' 11 [ l .-.- -.. 1 1 .74
.733 -.1380 -.1431 -. ** -.,", A1 ., i -. '. -. r -.i .d -.: -. ': -. 0WC6
.767 -.1158 -.1032 -.. ..''. .I i- -..':.' -.0458 -.0358 -.0448 -.0291
.800 .0432 .0474 .0461 .0513 .0510 .0562 .. ... ..... r .0512 .0499 .0367 .0518
AP .0827 .0834 .0857 .0863 .0896 .0951 .0973 .0941 i I .' .0652 .0619 .0643 .0813 .0903 .0910 .0884 .0716 .0807
., .1125 .1126 .1157 .1145 .1176 .1174 .120 .1184 .. : .I .0902 .0910 .1028 .1172 .1182 .1133 .1095 .0968 .0999
.900 .1559 .1544 .1552 .1524 .1533 .1524 .1533 .1514 .900 .1517 .1531 .1615 .1598 .1606 .,. .'7- .1482 .1500
.933 .1511 .14851 .1456 .1456 .1379 .1437 .1437 .1437 .i- .933 .1959 .1841 .1702 .1618 .1481 .1-.,.. .Iv"1 .1647 .1712


C 1 F I DEfI IAL








NACA RM L53H04


CONFIDENTIAL


TABLE I.- Continued



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL

(h) M = 1.02.


-a = 2.3 a 4.1

X/l A B C D E F H I X/I A B C D E F G H I

0.017 0.1958 0.1895 0.1981 0.2114 0.2277 0.2418 0. :.' 0.I!7 i 0. 775 ..:17 '.24 : .I'. '- i .. L 1. I : :..
.033 .1501 .1523 .1580 .1656% .1790 1-3- -' -34 ; *i. .: i .
.067 .0815 .0855 .0893 .091i .l016 .L.. 7;T 1371 .180 .> .-1- .I O I *:
loo.100 .04g91 .0578 .0o626 .o626 .0731 .,:,7 "6 .,: -, .@03 .i', ,:,:.ir .r... ,. .: .,. :' '3r ,-"
.133 .0291 .0187 .0197 -.0032 .0445 .0569 .0674 .0683 .0683 -,i .. .,'.
.1e7 -.0r., -..:?. -.035 -.017 -.0262 -.0176 -.00oo61 .0063 .0073 .,* 7 .: 58 :'. -.. .: .: `56- ,:, V 1* ..
.2 -..08, -.cot:- -.- -.0*Ik : -.0615 -.0538 -..0462 -.o0405 -.0405 'j 7 -. : 7-.) 3 *: m-:- -.:'- C7b -.. I'T,, ...-
.300 -.0899 -.0901 -.0910 -.0958 -.0939 -.034 -.0777 -0681 -.0691 -.:. .: ..r.. ... -. : .
.367 -.0774 -.0719 -.0729 -.0738 -.0729 -.0710 -.0662 -.567 -.0567 7 3 -.T -.
.433 -.0889 -.0901 -. 3 -. O? -..3) i -0., Ai ..- L. 07 -.C.796 .' -.' 7 ... ..: I:I -. : -..-- ,9 -. j. :
.500 -.0766 -.0767 -.J7'.' i. -.:'., -.: 60 5 -...7 :-767 r. : -.... ,: .W: o.
.5c7 -.. 0& -. k' -.y' -.0977 -.0958 -.0939 -.0929 -.0930 -: -' : .- ... 1 )6. 1 06-
.rIlI -.i- k }13 -..C'9 '102, ; j%.. :"*.6
.700 -..0C6 -.'C,:6 -., S -.. -. -. .. 0 -... -. > .x r. -
.7J3 -.0C 6i -.C08 : -..L -..106 .L I .' 2- 1 .Ad -..'*j -.,:-
.7 ; "Y i8 -." 7. .-. :' l = .., : = L 'I = .7. 7 -l 7. -.:'- -=.,. -.. -'

.8y0 ..z .:.4 1.. .. 33 .
.8,3 .3' 096 1 : .: : :.: .,:. .: .833 6 .8 0875 99 .5 1 02 101






.800 j .0 .A7 .j 1-

.800 .o096 .0732 .: .0952 .0926 .99 .0795 .0926 .8 .o 71 .I:072 ., 7: :-il

.7 .1303 133 .1310 .1 .1310135 3 .1053 .109 .I. .1. .. .
.067 .0969 .102688 .10267 ..1678 .1674 ., .1693 169 .693 90 .1616 .1619 .1660 .1628 .161 .1600 .1593 -1523 .1535
.100 .1599 .0731592 .15781 ..1573 .19 17 192 .16977 .9.3 1893 .1810 1.c1 .-9 .i .4161 .1650 1695 1793
.1 7 *.:-.. .0-. ., r-.? 1 '. .a .. .. : -.': .1:3- A, -. -. ..... :.. :, .. 5










. "1 'A. l .., .- .*rj,
. 1 :7 r A.. .. :: : .. .,
.'7,' -..:<;7 .O"9r,. -."..o4 -., 9cy -.. i7" ,. -, ". ,:" : .2 : -.107h ,. ,'-- .- *.." -. .. 0 ,- ,"*7
. t0 -.'1,7* : i?7' ...l.67 -. 9 .l -. .. C .. ,: 7, : ... .-, :, .. ., k 12.. ? -- I -, *.*-,J -.o:,
. .. -. -. -. -. -
.70n -. .032 .02 65 .0312 ..014 .0312 .05- 5- -. -. 8' '0 1 -. A' ,. .'.' :.7 A ..,.U
.733 W : j _J-.8'7 -.****X -. < O* -.*j6 3 -.*<.: .*' 7 8 .5 1 1 r. 16 .. *:1 -
.7c -.7i,, -." f : -.. _W _- .o ..6 -. ."- -.el*: .7 : 7 7 ; 0 .LA -i^ )t .7





. -. l l -. -. B -. .: -.. -. i -. -.0 ..- .7.87
.800 .0 .0321 .0265 .03120 .0245 .0255128.2 -0231 -.0157 &-. L : :0 .0.15
.833 .094O .0971 .095 5 .0952 o926 og .o .096 0952 .0926 ,.> ..-8.0710 .0722 A L
.867 .1303 .1334 .1310 .1315 .1 .13 .1300 13 1300 7 .1053 1094 : 7 .y. r .I
.900 .1676 .1688 .16 .167 678 .167 .1693 1697 .1693 .900 .1616 .1619 .166 .162 .1612 .1600 .1593 .1523 1535
.933 .1599 .1592 .1578 .1573 .1597 .1 .1597 .1592 .1569 .933 .1893 .1810 .1736 .1590 .1621 1 650 .1695 .1793

o 1.9 a8.5


.0 17 .I 1 i 5 .. :" : 'A .,



..3 o -1 -., .',, .., 0..., 2..,., 0. .. 1. -. ', .. ':i "' 1 : A.. -062.-- 051.
.807 o ot I ,: -.* i -. .r ,, .. : :.'.'.' 1:.r "0,, .0T, -...7 :,- I 3. 3'". .'. ,'A= -.02 037

.b3,X 0-.,). 7', -.C .,'), .00 ..:,' -.9 0 A [-. -. ,:,3, I 3 '-- -., : Ll' :,, ;- *.0788 ..u't




.800 .1 .13. 16.:,91 5 696 ,7 6.15 90 3 1 3 A A. 3 .0292 .037014
.86 .12 .1293 .1271 .1312.1291 .1351 .1300 .13601310 .867 .' i: 1112 1088
.933 .16 .163 .158 .1580 .1578 .1598 .159Q .1589 .15_ .933 2057 .197 .1816 .1646 162 1703 1701 .1789


CONFIDENTIAL








CONFIDENTIAL


NACA RM L53H04


TABLE I.- Continued



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL


(i) M = 1.05.


a = -2.3 a = 4.10

x/l A B C D E F G H I X/l A B C D E F G H I

0.017 0.2138 0.2069 0.2124 0.2265 0.2385 0.2564 0.2703 0.2872 0.83T' 17 0. ,:,. ..1 -' ', :7-I -. 'l3 0.2377 0.2154 0.2004 0.2005 0.1957
.033 .1691 .1705 .1741 .1835 .1928 .2059 .2161 .2302 1r. ..-.. : i. :'J3 8 .1864 .1678 .1574 .1556 .1509
.067 .1114 .1154 .1163 .1229 .1293 .1443 .1527 .1695 L-.:* ,c., .L'-' ,'- Ai'- ,j8 .1182 .1099 .1005 .1071 .1023
.100 .0881 .0958 .0976 .1004 .1079 .1135 .1228 .1294 .1265 .100 .1431 .1491 .1350 .1145 .0967 .0818 .0949 .0753 .0734
.133 .0723 .0594 .0622 .0771 .0845 .0976 .1079 .1107 .1079 .133 .1236 .1061 .0930 .0902 .0753 .0678 .0641 .0585 .0584
.167 .0034 -.0013 .0024 .0062 .0146 .'3'10 l n1 Wfl h. .167 .0565 .0473 .0360 .0192 .0052 -.0060 -.0097 -.0069 -.0060
.233 -.0348 -.0340 -.0321 -.0349 -.0274 -.. *'-. :' :.: ..- .,.c -.-'. o -. .. .' -. ;: i ..O'
.' -7- --- 7- .769 -.0657 -.0620 -.0405 -.0601 '" :, .. .
"- 66 -.0639 -.0601 -.0499 -.0508 .367 o5- -,8- 6. ,, .. 7. -0 0- .
.43 : '-. .- ..37 -.0853 -.0834 -.0741 -.0788 .433 '. -.' :- .: -. -. 1 -.. : =: :, -.. ,>
.500 -.o10 -.0984 -.1012 -.1021 -.1030 -.0993 -.0974 -.0919 -.0918 .500 -.0926 -.0929 -.1003 -.107-.1.124 -.1115 -.1059 -.1013 -.0993
S- '-.1087 -.1142 -.1171 -.1217 -.1189 -.1189 -.1189 -.Il. .567 -.1215 -.1200 -.1255 -.1312 -.1311 -.1246 -.1162 -.1115 -.1087
S-.1152 -.1198 -.1199 -.1236 -.1236 -.1254-.1255 -. .633 -.1373-.1321 -.1367 -.1349 -.1339 -.1265-.1180 -.172 .1143
m .-- -.1273 -.1338 -.1376 -.1441 -.1423 -.1441 -.1460 -.1469 .700 -.1532 -.1489 -. -. -.1564 -.1535 -.1414 -.1339 -.1312 -.1292
.733 -.1242 -.--,i -7.* -.1329 -.1487 -.1516 -.1618 -.1591 -.1637 .733 -.1700 -.1723 1648 -.1544 -.1368 -.1274 -.1181 -.1152
.767 -.1028 -.. *- .-i. -.1161 -.1301 -.1367 6-.106 -.1497 .767 -.1634 -.1676 -. 1517 -.1339 -.1153-.1059 -.1003 -.0975
.800 -.0348 -.0265 -.0386 -.0396 -.0564 -.0611 -.0760 -.0807 -,. -.1047 -.0966 -.0900 -.0732 -.0527 -.0321 -.0293 -.0219 -.0237
.833 .0760 .0874 .0743 .0836 .0724 .0846 .0659 .0743 .0575 x. .0509 .0604 .0594 .0725 .0753 .0818 .0762 .0781 .0743
.867 .1505 .1574 .1527 .1565 .1508 .1574 .1517 .1555 .1489 .867 .i .1454 .1481 .1491 .1462 .1482 .1453 .145 .1453
.900 .1971 .1994 .19'i .1994 .1993 .2031 .2031 .2059 .2040 .900 .- '.r .1957 .1911 .1901 .1893 .1892 .1883 .1892
.933 .2036 .2013 .1984 .1994 .1993 .1994 .2021 .2031 .2040 .933 .2093 .-*:. .2022 .1968 .1948 .1911 .1929 .1968 2060

a = -0.2 a = 6.20

0.017 0.2362 0.2337 0.2348 0.2430 0.241 .- ..... : .. : ... 0.017 0.3414 0.3266 0.2945 0.2631 0.2236 0.1883 0.1769 0.1771 0.1760
.033 .1877 .1936 .1937 .173 1 7 .196. .. 3 .033 .2809 .2743 .2441 .2061 .1713 .1444 .1340 .1342 .1349
.067 .1253 .1330 .1321 .1330 .1331 .' .1377 .1498 .067 .2073 .1977 .1723 .1332 .1023 .0856 .0817 .0893 .0911
.100 .1011 .1125 .1125 .1106 .1116 ...** .1097 .1153 .100 .1700 .1;- .1452 .1080 .0808 .0585 .0575 .0604 .0622
.133 .0745 .0761 .0761 .0892 .0901 .0966 .0967 .0957 .0920 .133 .1468 lo .0oo4 .0828 .0566 .0454 .0454 .0463 .0472
.167 .0173 .0155 .0164 .0192 .0202 .0229 .0239 .0313 .0295 .167 .0806 .0688 .0444 .0136 -.0125 -.0256 -.0274 -.0200 -.0181
.... -. .233 .0155 .0127 -.0088 -.0396 -.0592 -.0658 -.0610 -.0508 -.0480
..:..'. ,. .: -. :,. : :.. i8 .., .. .:, 11 .300 -.0320 -.0405 -.0601 -.0919 -.1077 -.1041 -.0937 -.0835 -.0797
S .. -. : .. : ... -- .367 -.0298 -.0405 -.0592 -.0826 -.0937 -.0966 -.0853 -.0751 -.0685
-.0862 -.0881 -.0871 -. -. : '". ,- '- .. .' :- : .... .1125 -.1217 -.162 -.1021 -.0947 -.0890
.500-.1019 -.0955 -.0984 -.0964 -. .' -.. .. .: ..,; .:. .''.-. I, -.1218-.1282 .1256-.1096-.1022-.0956
.567 -.1205 -.1123 -.1152 -.1142 -.1161 -.1132 -.1161 -.1160 -.1189 .- .. ",1- s' .180 -.1287 -.1358 -.1152 -.1007 -.o1030
.633 -.1270 -.1188 -.1.1 -.1170 -.1189 -.1170 -.1189 -.1207 -.1208 .633 -.1354 -.1358 -.1459 -.1536 -.1487 -.1 -.Iii" -.1A. 1 -.:i..'.
.700 -.1410 -.1337 -.1 -.1375 -.1414 -.1356 -.1385 -. .- .700 -.1522 -.1545 -.1637 -.1751 -.1665 -. i .....0 -.1330 -.1245
S1429 -.138 -1450 -.1384 -.145 -.421-.1487' -. .733 -.1736 -.1835 -.1889 -.1854 -.1609 -.1340 -.1208 -.1162 -.1021
..1224 -.1235 -.1273 -.1235 -.1292 -.1272 -.1329 -.- "I .767 -.-. --.1872 -.1889 -.1741 -.1376 -.1106 -.1002 -1059 -.0984
.800 -.051 -.0507 7- ..0554 -.0620 -.0545 -.0610 -. -. .800 -.. .1144 -. ... -. -. m. -.0312 -.0218
8 o .0676 .0789 --- .0733 .0677 .0808 .0715 .:*' .833 .0359 .0389 : ,,-, -., *,,*-- .0604 .0705
.1511 .1582 .1536 .1572 .1527 .1582 .1536 .867 .1291 .1304 .1377 39 .79 .139 .1342 .1340 .1276 .1340
.900 .. .2048 .2031 .2039 .2031 .2057 .2040 .900 .1952 .1940 .1947 .1865 .1872 .1865 .1891 .1809 .1844
.933 '. .2039 .2031 .2039 .2040 .2039 .2031 .':-- : .933 .2334 .2266 .2199 .2108 .2096 .2052 .2096 .2136 .2311

S= 1.90 a = 8.50

0.017 0.2697 0.2619 0.2581 0.2526 0.2441 0.2339 0.2283 0.2302 0.2264 0.017 0.3905 0.3660 0.3146 0.2607 0.2037 0.1618 0.1524 0.1563 0.1599
.033 .2157 .2171 .2152 ." ." .1993 .1835 .1797 .1798 .1779 .033 .3253 .3092 .2624 .2019 .1524 .1171 .1133 .1180 .1236
.067 .1486 .1499 .1489 i.' .1321 .1247 .1219 .1266 .1228 .067 .2453 .2280 .1869 .1246 .0816 .0593 .0630 .0761 .0816
.100 .1216 .1266 .1265 .1126 .1097 .0958 .- .0920 .0920 .100 .2025 .1963 .1552 .0966 .0583 .0313 ~. .0500 .0546
S .1030 .0892 .0873 .0920 .0883 .0846 ,-. .0762 .0761 .-- .1783 .1479 .1059 .0695 .0304 .0173 .7':;. .0323 .0369
.. .0359 86 .0230 .0174 .0136 .0099 .I .' .1122 .0938 .0518 I. '- I' 7iI I- I"I;.
.233 -.0153 -- -- .34 -.0162 -.0246 -.0228 -.0293 -. .233 .0369 .0304 -.0097 -. .- '- .:. .- r -
.300 -.0590 -.0536 -.0620 -.0666 -.0741 -.0666 -.0722 -.0676 -.0741 .30 **I .. -..1327 -. i.. I:*'' 1 i -..1
S 36 -.0564 -.0601 -.0638 -.0666 -.0676 -.0629 -.0629 .36 .- ": ,- "* .. -.1187 -.... -.. -.. -.: .
....34 -.0853 -.0881 -.0900 -.0872 -.0881 -.0862 -.0872 .43 ........ *- .- .. -.1448 -.1328 -.1047 -.0955 -.0814
.500 -.0954 -.0946 -.0956 -.0984 -.1002 -.1012 -.0993 -.0984 -.0974 .50 -.... -. -... 1495 -.1402 -.1094 -.1048 -.0889
.567 -.1205 -.1170 -.1180 -.1189 -.1180 -.1161 -133 -.1142 1 .1124 .567 -.1009 -.1113 -.1383 -.1682 -.1700 -.1449 -.1122 -.1160 -.0936
.633 -.1308 -.1264 -.1254 -.1226 -.1208 -.1198 -.1152 -.1189 -.1142 .633 -.1260 -.1318 -.1532 -.1747 -.1672 -.1384 -.4 -.1281 -.1029
.700 .1457 -.1432-.1413 -.1450 -.1413 -.1385 -.1 -- .. .700 -.1446 -.1 -,1718 -.1943 -.1783 -1402-. 1430 -.1131
.733 -.1540 -.1590 -.1543 -.1506 -.1 -.-.145 .1413 669 -. .' '" 7 -.1625 -.1262 -.131 -.1 .8
.767 -.1401 -.1488 -.1422 ,' I .:.* -.l .. .767 -.1753 -.1943 -. "1 1 -.1336 1':" -? 3 _- .
.800 -.O777 -.0816 -.685 -.0' i .800 -.1223 -.1262 -.1159 -.0964 -.0367 .' ..... '.-..., -..i
.833 .0639 .0556 .0687 .0584 .0743 .0706 .0. '** ..... .833 .0313 .0201 .0471 .0481 .0704 '. ..;- '
.867 .1514 .14 .1545 .1499 .1545 .1499 .1' i .867 .1346 .1311 .1459 .1469 .1506 ': : .
.900 .2045 .2031 .2049 .2012 .2012 .2003 .2 .900 .2099 .2085 .2149 .2066 .2102 :' ': '"r .
.933 .2054 .2040 .2031 .2022 .2021 .2003 .20C* I .-33 .2537 .2439 .2335 .2215 .2186 .:: .:.'


'01iF I DELTA 1LA L








NACA RM L53H04


CONFIDENTIAL


TABLE I.- Concluded



PRESSURE COEFFICIENTS OF A 120-INCH FINENESS-RATIO-12 BODY OF

REVOLUTION IN THE LANGLEY 16-FOOT TRANSONIC TUNNEL

(j) M = 1.09.


.= -2.4 a = 4.10

x/I A B C D E F G H I x/Z A B C D E F G H I

0.017 0.2011 0.2014 0.1968 0.2253 0.::- :. :.' : : :. :, .: 7- ,n '7 0.2940 0.2798 0.2668 0.2504 0.2245 0.2080 0.1913 0.2006 0.1895
.033 .1634 .1682 .1646 .1830 `:. :,'.17 1 :- j .2398 .2366 .2235 .2034 .1821 .1656 .1526 .1564 .1462
.067 .1064 .1103 .1048 .1130 .1131 .1333 .1379 .1655 .1600 .067 .169 .1656 .1517 .1334 .1131 .1030 .1011 .1076 .1029
.100 .0458 .0744 .0707 .0799 .0808 .0946 .0956 .1176 .1085 .100 .1157 1"06 1i9 .01"6 07'w0 061' w "O'n .0495
.133 .0577 .0477 .0422 .0670 0689 .0882 .0919 .1020 .0974 .133 .1083 ..*- *,: ,;;i .'- I '.'. .0477
.167 .0145 .0017 .0017 .0140 .0210 .0145 .0201 .0578 .0578 .167 .0633 0.'. ,),, i' '6 '1, ':., .0072
.233 -.0305 -..02 41 0241 -.:. .. :. .... .... ..- .0099 .233 -.0002 4.'. '1 '' '* '..* e .0260
.300 -.0471 -.0499 -.0499 ...=. .' .l. 0' -.O23 .300 -.0223 -.'.,'.7 l'' -' ,', .. ,i ," -.0527
.367 -.0262 -.0260 -.0315 -.'...; *: 7 ,:I -.0195 .367 -.0084 -...: ..,L~,.'. :. ,., ,.'- 4. *. .:'., ..0296
.433 .0081 -.0048 .0090 .0044 .0090 .0320 .0044 .0477 -.0011 .433 .0743 .0625 .0587 .0284 .0238 .0053 .0109 .0044 .0118
.500 -.0425 -.0490 -.0370 -.0664 -.0517 -.0545 -.o296 -.034 -.0195 .500 -.0397 -.0426 -.040-.0748 -.072 -.0693 -.0563 -.0582 ..0481
.567 -.0921 -.0931 -.0932 -.1069 -.1088 -.1152 -.1088 -.1171 -.1097 .567 -.1114 -.1126-.107-.1255 -.1180 -.1162 -.1015 -.1024 -.0932
.633 -.1233 -.1226 -.1263 -.1309 -.1337 -.1318 -.1318 -.1281 -.1291 .633 '63 .-i0- i`.., -.1457 -.1420 -.1365 -.12)4 -.1255 -.1180
.700 -.1481 .1447 -.1493 -.1557 -.1622 -.1594 -.1622 -.1649 -.1659 .700 i.7 77 -.1770 -.1714 -.1595 -.1475 -.1494 -.1429
.7 I -jr. ':: .- :- .1576 -.1733 -.1796 -.1880 -.8 -.1889 .733 -.1887-.1945 -.1935 -.1909-.1788-.1641 -.1493 -.1457 .1401
7 ..1l: ... ..- -A ..1539 -.1714 -.1695 -.1852 -.1898 -.1963 .767 -.1979 -.2047 -.199-.1.1899 -.1723 -.1549 -.1401 -.1384 -.1328
.J. ,....0 ...'.' : 'li -.1069 -.1217 -.118 -.1' < ii I1 .800 -.1510 -.1476 -.i. 0I 0 I:' o03L ,. i' 'j i. v.
.833 -.0627 -.444 -.059 -.0628 -.0757 -..-"' .. -.*','.. .. ." ".: r. r.L -'. 7:... ." 573 = ; r-
.867 -.0020 .0099 -.0057 .0164 -.0039 .0090 -.0177 .0035 -.0232 .:' 4 .... ** .0035 .0072 .0247 .0053 .0044 .0053
.900 .0788 .0992 .0808 .0964 .0827 .1001 .0873 .1103 .0900 .,,':. .L- .,.- ..- .0947 .0910 .0919 .0873 .0882 .0864
.933 .1211 .1351 .1158 .1305 .1167 .1333 .1195 .1379 .1232 .933 .1387 .1380 .1324 .1269 .1250 .1232 .1232 .1288 .1379

a = -0.20 a = 6.20

0.,,7 O 40 :1 :. 0.? .3 1 -' i" *.. _.? I 7 447 0.2595 0.2539 0.017 0.3297 0.3144 0.2815 0.2500 0.2060 0.1829 i-. i7 ,.
I.':. .I *~; 1. Q;: i... 7 :. 14 .2042 .2060 .033 .2709 .2666 .2355 .1985 .1628 .1424 i, .. i' ...
.':', i i'-'. i;. .: .1.7 124 .1453 .1453 .067 .1946 .1893 .1609 .1231 .0882 .0799 ''7r I' i '..a
.100 .0577 .0864 .0910 .0864 .0910 .0864 .0891 .0956 .0928 .100 .1432 .1562 .1305 .0937 .0606 .0440 .0330 .0431 .0366
.13 .0678 .0560 .0587 .0735 .0762 .0827 .0864 .0836 .0827 .133 .1340 .1121 .0827 .0679 .0422 .0394 .0357 .0375 .0366
'.7 .0255 .0099 .0145 .0210 .0265 .0081 .0118 .0403 .0403 ..167 .0862 .0605 .0385 .0173 -.0057 -.0351 -.0333 -.0057 -.0048
.233 -.0250 -.0195 -.0131 019- o01 ..0140 -.0085 -.0076 -.0039 .2 '.' e. "' 11 ... '.r .ll
.300 -.0425 -.0471 -.0398 -, *,.r .'i., 8 j.1 -.0398 .3-' -...* -.. 7. ): -. .*" .- -.'.. 4, .
.367 -.0293 -.0287-.0223 -.03-.02.0260 *3'" 0' :b7.. -.0232 .3'7- '.*' <. -r .-... C .-_i.. W. :-I
.433 .0210 .0118 .0210 .0192 .0330 *'"* C.L77 : .0495 .4., '-, ..7 i o.u .' ::' .. 1 .'*l :.:I
.500 -.0507 -.0499 -.0425 .....4, .'545 -.0444-.0 508 -.444 50 .5 ". "' ..,' .. ..A.
.567 -.1022 -.1033 -0978 -.1107 -1051 -.1134 -.107 -.1162 -.1107 .5' ': ; i, :.',,* i: 44. .' .. 7 '.,
.633 -.1279 -.1319 -.1282 -.1337 -.1272 -.19 .-.1254 -.1309 -.1235 .633 -.1344 -.1400 -.1549 -.1603 -.1622 -.1455 .1263 -.1235 -.1162
.700 -.1536 -.1558 -.1512 -.1604 -.1567 -. 1 1530 -.1622 -.1567 .700 -.1702 -.1713 -.1816 -.1934 -.1880 -.1621 .1493 -.1455 -.1410
.733-.160 .1678 -.167 31 -.1696 -.1677 -.1733 -.1687 -.1742 -.1677 .733 -.1941 -.2007 -.2119 -.2081 -.1926 -.1603 -.1493 -.1400 -.1309
.767 -.1527 -i -.1585 -.1632 -.1604 -1687 -.1641'-.1696 -.1631 .767 -.2134 -2201 -.2239 -.2090 -.1816 -.1455 -.1392 -.1373 -.1364
.80 -.106 1070 -.1162 -.1125-.1144-.1107 -.1355 16 .8o00-.1702 -.1621-.1622 -.1437 -.1189 -.1014 v- 1-'.
.833-.061 -.0628 -.0609 -.0702 .0655 -.0692 .0665 -.0757 -.0702 .833 -.1077 -.1032 -.1005 -.0830 .0674 -.0572 '- .7
.867 .008 .0053 .0109 .0044 .0090 .0035 .0081 -.0002 .0053 .867 -.0397 -.0296 -.0214 .0007 -.0029 .0007 -.0112 -.0094 -.0131
.900 .104 .0983 .1029 .0993 .1048 .1011 .1066 .1011 .1048 .900 .0779 .0891 .0827 .0863 .0762 .0835 .0725 .0771 .0679
933 .1386 .1343 .1379 .1352 .1398 .1352 .1389 .1361 .1398 .933 .1514 .1516 .1361 .1332 .1241 .1305 .1250 .1387 .1499

S= 1.90 = 8.5

5 01:7 ?:,~ C, 513 0.24840 1.; iB ', .. 0, I.:.i ... :' 17: 0 1 8 3738 0. .3' :, 0. .1829 '' 0.1461
3' 1 2'.i> '117 .2088 .: 4: '. 3r' i', I ', 1 : 6 .y .4 7- I ': L "1 .1369 .L111 i i .1111
.067 .1433 .1454 .1425 L'. i' i .' ,7 .'-*9 ..: i r't .0596 .0495 .0504 .0762 .0743
.100 .0780 .1104 .1066 .0965 .0900 .0781 ..';I .0744 .0735 .100 .1762 .'0, i'-9 "r ."' 7 .0173 .0164 .0302 .0283
.133 .0844 .0717 .0689 .0772 7'7" o'- 0 ."7ir .0643 .0652 .133 .1624 .14 i :." .0127 .0173 .0256 .0283
.167 .0412 .06 6.0256 .0256 .'.-_ .i:<' -.o0002 .0219 .0238 .167 .1119 .0808 .0403 '-' I '..
.1j 4l. -.0076 -.0057 -.0158 -.0149 -.0204 -.0168 -.0186 -.0131 .233 .0384 .0357 -.0011 0- *:7r '~'I .l': :':4.
., -'1 'j -.0370 -.0342 -.'.'." i': a., ...l :.'7 -'. 7- .300 .0118 -.0029 -.0370 r- ,,- ..'..
?7 0 -.0223 -.019 --..:7 ,:',:, ,',r 367 .0314 .0017 -.0305 ; .I'" '- 'j 4d8 '.:r
.433 .0449 .0302 .0385 .0219 .0293 .0192 .0274 .0210 .0284 .433 .0834 .0753 .0247 .'', '"-2. ? -*: -'' ''
.500 -.0508 -.0490 -.0425 -.0674 -.0628 -.0628 -.0536 -.0591 .0499 .500 -.0140 -.0259 -.0554 A A 7 .. I .
.567 -.1096 -.1089 -.1033 -.1144 -.1070 -.1107 -.1015 ..1080 -.1015 .567 -.0948 -.1041 -.1281 ir i i'. .. .- I v L"- 7'
.633 -.1326 i- -' .. i8 -.1347 -.1291 -.1282 -.1226-.1264 -.1199 .C,, -. 1. -.1676 4,-: I I l *r
.700 -.1611 -.i..- i' -.1641 -.1585 l. ..7 .1540 -.1475 7. -.1952 i]' .. F- : .-. : .
.733 -.1740 -.1789 7'. -.1752 -.1659 ;':' -.1549 .1493 .733 -.1913 -.2063 -.2265 -.2283 -.1971 -.1557 -.1465 -.1409 -.1244
.767 -.170 -.1807 -.17 4' -.1715 -.1604 '. ..1476 -.1420 .767 -.2179 -.2320 -.2421 -.2302 -.1777 -.1465 -.109 -.1566 -.1465
.800 -.='. I. iL; ..i89 -.1' ."9 11?"= 1061 '3? n.? -.0941 .800 -.1793 -.1768 -.1768 -.1575 -.1143 .'' I *" '
.8 i 07'.' ..:' .; ". -.:.71: .:. : .'= i .'.'. -.0527 .833 -.1150 .1143 -.1106 -.0885 -.0664 ... AI '7' ,. '.
.': i .0035 .0090 .0072 .oI0c .*1 .0164 .0109 .0155 .867 -.0507 -.0480 -.0287 -.0057 -.0048 -.0oo85 -.0177 -.0259 -.0269
.900 .1074 .1085 .1094 .1076 i:,'l .1048 .1039 .1048 .900 .825 .0891 .0955 .0937 .0909 .0891 .0845 .0799 .0753
.933 .1405 .1398 .1398 .1371 .1379 .1361 .1361 .1371371 379 .933 .1808 .1737 .1590 .1470 .161 .1433 .1461 .1553 .1682

NACA
-A--\n~


CONFIDENTIAL









CONFIDENTIAL


NACA RM L53HO5


wc,
0



I-I







4-4



00
01

S()
4-~
o o





I

U
4-3
a)
a)Q0
01)









4 -
W















F-l
CH












s-4


CONFIDENTIAL








NACA RM L53H04











































o


CONFIDENTIAL


CONFIDENTIAL


d



0-
o
0





4

0


0
c d





o -

Eo








4-3
0


4- -)
rio







0r
-rl


0

O








NACA RM L53H04


Center of rotation


Long cone
-2"
- --- i


- 375"- -


1=120"


71.25-


Center of rotation -10"max diam 2"

--- 2 "


90
- 60" 503" /


= 120"


180 1575
H


F 1125


Short cone


Angular positions
of orifice meridians
looking upstream


General transonic


E 90

/ D 67 5

C- 45
B
A
S225
fuselage ordinates
fuselage ordinates


x/1 y/Z x/l y/l
0 0 0.4500 004143
0.005 0.00231 5000 .04167
0075 .00298 5500 04130
0125 .00428 .6000 04024
0250 .00722 6500 03842
0500 .01205 7000 03562
0750 .01613 7500 03128
.1000 .01971 8000 02526

.2000 .03090 8500 .01852
.2500 .03465 9000 01125
7.I i ?'4'0iI C,"'4 r, 0
,4000 I -I I_ _i I .040'6 3
4000i .04063 I


Leading edge radius = 00051


Orifice locations

x/l x/l
0.017 0.567
.033 .633
067 .700
.100 .733
.133 .767
.167 .800
.233 .833
.300 .867
.367 .900
433 933


NACA
*- i A


i


(a) 120-inch body.

Fil7:.r- 53.- Dimensions and details of models tested in Lirngley 16-foot
transonic tunnel.


C'oTJFI FIENTI AL


- x -


CONFIDENTIAL


--c------
Y ~I. ..


411 ------ -








NACA RM L55H04







60


CONFIDENTIAL


I00, 268




/ \1000 mox dia
-500 -431
iCenter of rotation


--33-33-

-20-
-~" -~II ~~ -I-


--- 1-67




-333 max dia
333 max dio


ZCenter of rotation


180O


75*
'45o


100-inch body
Orifice locations
x/ Z= 120"
0.017 0433
.033 467
067 500
.100 533
133 .567
.167 600
200 633
.233 .667
.267 700
.300 733
.333 .767
.367 800
400


Angulor positions of orifice meridians

33 33-inch body
Orifice locations
x/l 1= 40"
8= 0,45, 135',180 8= 75,1050
00625 0.1625
.1125 2125
.1625 2625
2125 .3125
.2625 3625
3125 .3875
3625 4125
4125 4375
4625 4625
5125 .4875
5625 5125
6125 5325
6625 .5625
7125 5875
7625 6125
8125 6375
6625
7125




(b) 100- and 3355. -inch bodies.


Figure 5.- Concluded.




CONFIDENTIAL








CONFIDENTIAL


0


0 C


0
0
/IV U
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IFy *uoyi,^T~p eosjjne


NACA RM L55HO0


C (l


*0O
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0


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0
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0
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*

o8BJAV


CONFIDENTIAL









NACA RM L55H04


CONFIDENTIAL


qJ6ual Apoq jo 4ool jad jaqwunu sploui(al a6oJAV-


CONFIDENTIAL


0


Q)











0 0
.-4-




to











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NACA RM L53H0O


O








0n
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.70NF I ENTIAL







NACA RM L55H04


-2 --Ti ]i tT

r'
j ,._ '


2 -


-. : I iI."


j 120 body
0 100" body I
' >3333" body


'


-1


2 .- -


C 41 1
4]---I---------I-I-I-------------------
o?-- ------------------- ----------------


I_, L_ i: I1


2 0 -


4a 80


A. fl t~- ;.t a~~' I


-- -' -
I I | I | I |I| i .




Y R.


T--1
bJE 0 ~ ~ ~~


0 1
Fraction of body length x/l


*1-


(a) M = 0.60.

Figure 6.- Comparison of pressure c'-efficients over the three bodies
with angle of attack. Plain symbols are 1800 meridian and flagged
symbols are 0 meridian.


CONFIDENTIAL


C


2


-2


C,


--


I


C('IT-IDETTILA


i i .j


T-....


11 II








CONFIDENTIAL


NACA RM L53H0l


-2 ------- -I---I-------------1---4 ---I



o 120" body
o 100" body
C -' -o --- 3333"body




-2


S--i ,.. -




a 12




So 8 28
2











-2 T -
so- ---- -- -
A - --
























0
Fraction of body length, x/1
"Ji i I-_________ I I _________________________


(b) M = 0.95.
-- ..-'.1-..----
.. -e '- .





2 [ J

A N---
....---.------- ----- ----- ...---.----.



S- .- .

Fraction of body length, x/l


(b) M = 0.95.

Figure 6.- Continued.


CONFIDENTIAL







NACA RM L53H04 C,-FIIILTTIL 51



-2T







4._______--_____--0b
4 01o20" body
10 0"body
----- 3333"body-
a a 50

-2









4 --
-+-- --
-2 ---- 2-
2 [ .. -. _
2 r-- .










1 2 *

4. I ', r 4






-2[ -
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,,--_ _._.' '.__'_8








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S" -C I--'-E--
I. ,


S,----a --






2 t




,-4- ..AC .




-i "9 O10

Froction of body length x/9



(c) M = 1.00.


Figure 6.- Continued.



CONFIDENTIAL








CC ['T ,IEI ETIAL


NACA RM L55H04


2 -


-C 120" body
4 ---- t i

4. 100" body
--- 3333"body
15 I5



-2r -






6 120- -

S- -- -




6 Q -;i. -
ma


* 1 --


Bio
o _I 4.
" A U


;.
" *'-


+ -
S' .
r7




-2 .... .....
---- ---- -------- z


*sonir e
t


S ....i


NAC4


Froction of body length, x/



(d) M = 1.02.


Figure 6.- Continued.



CONFIDENTIAL


0L

c
a,


i







NACA RM L53H04


4 r _.... ________ -
, I ,_. ., -
l-.~' .... ".


.2------+-- -------- ----- -------- -L -Q -r- '^ ---
2 ---120 body
.o. 100" body
Sa= 8 33 3" body

-2 Q _- -- --- -I -- I ________ I ___
.4 --








-2' -






4"___" -,- -
-2


r


P '
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4 2



0 .2 .3
Froc


Q = IcI
4 .5 .6
tion of body length, x/7


.7


8 -r9 -

8 .9 1.0


(e) M = 1.05.

Figure 6.- Continued.










CONFIDENTIAL


CONFIDENTIAL


~i tti






NACA RM L5HL


.. .-.------ ------ ---'-"-----

C 4


.2 -n
.' I --,40
S-, ,, ... -. .-.- -


-2


SI !
ne 1 Ii r


--NACA -


0 .2 .3 4 .5 .6
Fraction of body length, x/l


7 .8 .9 1.0


(f) M = 1.09.

Figure 6.- Concluded.


CONFIDENTIAL


so


-


C,,ir TFIL-T, I/rAL


----- -----. .- O".-^ -
*, k 0 '^







NACA RM L53HO4


CONFIDENTIAL


-.20



-.10


faired point




1.00

0r --r---~--_ faired point

0

------------ -- --.95


--- ------_. feired point
0r
o





0
.20 ---.6







.o 0 -- -- ------i

--- -- -- -- -- -- -- -- -- -- --- --- --- --- --'^N Aca, 7 -
0 -- -- -- -- -- -- -- -- I -- -




0 20 40 60 80 100 120 140 160 180

Meridian angle, e



Figure 7.- Circumferential pressure distributions at one body station
(x/Z = 0.10) for four Mach numbers at 80 angle of attack.


CONFIDENTIAL








CONFIDENTIAL


-.20


NACA RM L55H04






















= 0.61


M

1.02



= 0.36



1.02




= 0.61


S100


1.00


Meridian angle, 9


Figure .- Circumferential pressure distributions at two body stations
(x/Z = 0.56 and 0.61) for two Mach numbers at 80 .ngle of attack.


CONFIDENTIAL







NACA RM L53H04


z U I
o 100" body


C.
.2


o


u? .9
0
o



E
0 NACA
z
0
8 .9 1.0 I.I

Mach number, M


Figure 9.- Variation of the normal-force coefficient with Mach number
of the 100- and 35.33-inch bodies at 80 angle of attack.
"0 _____


CONFIDENTIAL


CONFIDENTIAL








NACA RM L55H04


_ __-7-_ -- -

'--4
LI I H'

x/ 0 633



^ ___--------_____- --. ---- ---- -, -















i i
.--


















Si ,4160 180

Meridian angle ,


Figure 10.- Incremental-pressure-coefficient distribution with radial
angle at 80 angle of attack for two different bodies.









,TNrFIE',FTIAL


CONFIDENTIAL








NACA RM L535H0


CONFIDENTIAL


o 0 o
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UNIVERSITY OF FLORIDA


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UNIVERSITY OF FLORIDA
DOCj_.UMENTS DEPARTMENT
120 M.,RSTON SCIENCE LIBRARY
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