Research abstracts and reclassification notice

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Title:
Research abstracts and reclassification notice
Running title:
NACA research abstracts and reclassification notice
Physical Description:
37 v. : ; 27 cm.
Language:
English
Creator:
United States -- National Advisory Committee for Aeronautics
Publisher:
National Advisory Committee for Aeronautics
Place of Publication:
Washington, D.C
Publication Date:
Frequency:
irregular
completely irregular

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Subjects / Keywords:
Aeronautics -- Abstracts -- Periodicals   ( lcsh )
Genre:
federal government publication   ( marcgt )
abstract or summary   ( marcgt )
serial   ( sobekcm )

Notes

Statement of Responsibility:
National Advisory Committee for Aeronautics.
Dates or Sequential Designation:
No. 94 (Jan. 11, 1956)-no. 130 (Sept. 30, 1958).
General Note:
Title from caption.

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 001469325
notis - AGY1018
oclc - 14184154
lccn - 86657026
sobekcm - AA00005288_00001
Classification:
lcc - TL501 .U5895
System ID:
AA00005288:00001

Related Items

Preceded by:
Research abstracts
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Publications announcements

Full Text




National Advisory Committee For Aeronautics

Research Abstracts


and

Reclassification Notice


JAN9ARY 24, 1956


CURRENT
NACA RESEARCH REPORTS

NACA Rept. 1202

CHARTS RELATING THE COMPRESSIVE BUCKLING
STRESS OF LONGITUDINALLY SUPPORTED
PLATES TO THE EFFECTIVE DEFLECTIONAL AND
ROTATIONAL STIFFNESS OF THE SUPPORTS.
Roger A. Anderson and Joseph W Semonian. 1954.
ii, 19p. diagre., tabs. (NACA Rept. 1202. Super-
sedes TN 2987)

The stability of a plate under edge compressive
stress is analyzed in terms of the deflectional and
rotational stiffnesses of one or more longitudinal
lines of support between the plate side edges. The
results are presented in the form of charts which
make possible the determination of the compressive
buckling stress of plates supported by members
whose stiffness may or may not be defined by ele-
mentary beam bending and twisting theory but yet
whose effective restraint is amenable to evaluation.
The deflectional and rotational restraint provided by
longitudinal stiffeners and full-depth webs is dis-
cussed, and numerical examples illustrate the
application of the charts to the design of wing
structures.


_j
@-J
h 7,


NACA Rept. 1204 V

APPLICATION OF SEVERAL METH OR
TERMINING TRANSFER FUNCTIONS A
QUENCY RESPONSE OF AIRCRAFT FROM FLIGHT
DATA. John M. Eggleston and Charles W.
Mathews. 1954. ii, 24p. diagrs., Labs.
(NACA Rept. 1204. Supersedes TN 29971

A study is presented of several methods for deter-
mining the transfer functions and frequency response
of aircraft from flight tests. Results obtained from
experience in the use of these methods are compared
as to time required for application, comparative
accuracy, and means for facilitating their use. The
studies cover three categories of methods: sinus-
oidal response, Fourier analysis of transients, and
curve-fitting analysis of transients. Three general
types of aircraft are used to illustrate the application
of these methods.


NACA Rept. 1205 '"

A WIND-TUNNEL INVESTIGATION OF THE EF-
FECTS OF THRUST-AXIS INCLINATION ON PRO-
PELLER FIRST-ORDER VIBRATION. W. H. Gray,
J. M. Hallissy, Jr., and A. R. Heath, Jr. 1954.
ii, 37p. diagrs., photo., tab. (NACA Rept. 1205.
Supersedes RM L50DI3)

Data are presented on aerodynamic excitation of
propeller vibration with the thrust axis at two angles
of inclination to the airstream. Aerodynamic ex-
citation is calculated and compared with measured
values for several conditions Measured and cal-
culated blade vibratory stresses for several excita-
tion values are presented. The calculated values of
exciting force compared well with the measured
values at low rotational speeds but not so well at
high rotational speeds.

NACA RM E55129

PERFORMANCE CHARACTERISTICS OF CYLIN-
DRICAL TARGET-TYPE THRUST REVERSERS.
Fred W. Steffen and Jack G. McArdle. January
1956. 40p. diagrs., photo. (NACA RM E55129)

From tests on cylindrical target-type thrust re-
versers, it was found that the reverser frontal area,
lip angle, end-plate angle, and end-plate depth had
important effects on reverse-thrust performance.
Frontal area, reverser depth, lip angle, and end-
plate angle had important effects on the spacing re-
quired for unrestricted nozzle flow For reverse-
thrust ratios greater than 64 percent, the reversed
flow attached to the 70 cowl in quiescent air. Swept-
type cylindrical reversers were generally unstable.
The thrust-modulation characteristics of a cylin-
drical target-type thrust reverser were found to be
satisfactory.

NACA TM 1401

DIRECTIONAL STABILITY OF TOWED AIRPLANES.
(Die Seitenstabilit'a eines geschleppten Flugzeuges).
W. Sohne. January 1956. 53p. diagrs., tab.
(NACA TM 1401. Trans. from Ingenieur-Archiv,
v.21, no.4, 1953, p. 245-265)

A theoretical investigation of the lateral dynamic
stability of an airplane towed by a single towline is
presented, and the equations of motion are derived.
The effects of variations of towline length, attach-
ment point, lift coefficient, model mass, and angle
of climb are examined In addition, the effects of
changes in dihedral, tail area, and damping in roll
are studied


'AVAILABLE ON LOAN ONLY
ADDRESS REQUESTS FOR DOCUMENTS TO NACA, 1512 H ST, NW
THE REPORT TITLE AND AUTHOR.


WASHINGTON 2s. D C. CITING CODE NUMBER ABOVE EACH TITLE


NO.95


SA<36 HZ







2

NACA TN 3490

EXPERIMENTAL AND CALCULATED TEMPERA-
TURE AND MASS HISTORIES OF VAPORIZING
FUEL DROPS. M. M. El Wakil, R. J. Priem,
H. J. Brikowski, P. S. Myers, and O. A. Uyehara,
Wisconsin University. January 1956. 82p. diagrs.,
photos., tab. (NACA TN 3490)

Experimental and calculated mass and temperature
histories of drops vaporizing with a constant velocity
relative to the air velocity are compared herein, and
it is confirmed that, under many conditions, the un-
steady state or time required for the drop to reach
the wet-bulb temperature is an appreciable portion of
the total vaporization time. Work was done to veri-
fy or disprove the assumptions used in the computa-
tions. Data are presented to show that the assump-
tion of infinite thermal conductivity is valid pri-
marily because of circulation inside the drop.



NACA TN 3534

INSTRUMENTATION FOR MEASUREMENT OF
FREE-SPACE SOUND PRESSURE IN THE IMMEDI-
ATE VICINITY OF A PROPELLER IN FLIGHT.
William D. Mace, Francis J. Haney, and Edmund
A. Brummer. January 1956. 16p. diagrs.,
photo. (NACA TN 3534)

Instrumentation suitable for the measuring, record-
ing, and subsequent harmonic analysis of the free-
space sound pressures in the immediate vicinity of
an airplane propeller at flight Mach numbers up to
0.72 is described. The dynamic range of the equip-
ment is 150 to 113 decibels (re 0.0002 dyne/cm2) and
the system frequency response is flat within t1 dec-
ibel from 80 to 1,000 cps. Maximum second-
harmonic distortion is less than 3 percent for a
sound level of 140 decibels, and the overall accuracy
is +2 decibels.



NACA TN 3545

INVESTIGATION OF THE EFFECT OF SHORT
FIXED DIFFUSERS ON STARTING SLOWDOWN
JETS IN THE MACH NUMBER RANGE FROM 2.7
TO 4.5. John A. Moore. January 1956. 32p.
diagrs., photos. (NACA TN 3545)

An investigation was made at Mach numbers of 2.7,
3.0, 3.5, 4.0, and 4.5 to determine the effect of
short fixed convergent-divergent wedge diffusers on
the starting characteristics of blowdown jets ex-
hausting to the atmosphere. Wedge diffusers that
were extensions of the nozzle contours reduced the
overall pressure ratios required for starting to less
than one-half the values obtained without a diffuser.
The minimum overall pressure ratio required for
starting at each Mach number was about twice the
value predicted by one-dimensional theory.
Central-body diffusers were not so effective in re-
ducing the overall pressure ratio for starting as
were the wedge extensions of the nozzle, except at
the higher values of diffuser minimum area.


NACA RESEARCH ABSTRACTS
AND RECLASSIFICATION NOTICE NQ95

NACA TN 3552

INVESTIGATION OF THE COMPRESSIVE
STRENGTH AND CREEP LIFETIME OF 2024-T3
ALUMINUM-ALLOY PLATES AT ELEVATED TEM-
PERATURES. Eldon E. Mathauser and William D.
Deveikis. January 1956. 40p. diagrs., photos.,
tabs. (NACA TN 3552. Supersedes RM L55Ellb)

The results of elevated-temperature compressive-
strength and creep tests of 2024-T3 (formerly 24S-
T3) aluminum-alloy plates supported in V-grooves
are presented. The strength-test results indicate
that a relation previously developed for predicting
plate compressive strength at room temperature is
satisfactory for determining elevated-temperature
strength. Creep-lifetime results are presented for
the plates in the form of master creep-lifetime
curves by using a time-temperature parameter that
is convenient for summarizing tensile creep-rupture
data. The use of time-dependent stress-strain
curves obtained from plate-creep curves for pre-
dicting plate-creep failure stresses is investigated.






NACA TN 3553

COMPRESSIVE CRIPPLING OF STRUCTURAL
SECTIONS. Melvin S. Anderson. January 1956.
31p. diagrs., tabs. (NACA TN 3553)

A method is presented for calculating crippling
stresses of structural sections as a function of ma-
terial properties and the proportions of the section.
The presence of formed or anisotropic material is
accounted for by the use of an effective stress-
strain curve. The method of analysis applies to
many sections for which a procedure for calculating
crippling was not previously available.





NACA TN 3560

SPONTANEOUS IGNITION STUDIES RELATING TO
LUBRICANTS OF REDUCED FLAMMABILITY
Kenneth T Mecklenborg, Cincinnati University.
January 1956 17p. diagrs., tabs. (NACA TN 3560)

Increased interest in the use of diesters as lubri-
cants has suggested a study of the influence of the
structure of the alcohol moiety on the spontaneous
ignition temperature of a series of dialkyl azelates.
The determination of spontaneous ignition tempera-
Lures has been extended to a number of representa-
tive organic phosphorous esters with predominantly
aliphatic structures. Determination of the change
in spontaneous ignition temperature with composi-
tion has been carried out with hydrogenated polyiso-
butylene in combination with a siloxane and with a
phosphonate. The synthesis of polyisobutylene in
the lubricant molecular weight range has been
improved in yield.






NACA RESEARCH ABSTRACTS
AND RECLASSIFICATION NOTICE NQ 95


NACA TN 3571

LIFT HYSTERESIS AT STALL AS AN UNSTEADY
BOUNDARY-LAYER PHENOMENON. Franklin K.
Moore. November 1955. 32p. diagrs., tab.
(NACA TN 3571)

With the problem of rotating compressor stall in
view, an unsteady boundary-layer calculation is
made to find the unsteady increment of lift of a
stalled elliptic airfoil in a flow of time-dependent
incidence. The analysis indicates a counterclock-
wise hysteresis loop of the lift curve, the various
forms of which are discussed.


NACA TN 3581

EXPERIMENTAL INVESTIGATION OF BLADE
FLUTTER IN AN ANNULAR CASCADE. J. R. Rowe
and A. Mendelson. November 1955. 24p. diagrs.,
photos. (NACA TN 3581)

Compressor-type annular cascades of airfoils were
investigated to determine effects on flutter charac-
teristics of varying angle of attack, blade chord and
spacing, number of blades, and air velocity. Strain-
gage, pressure-probe, and hot-wire-anemometer
instrumentation was used. Large-amplitude sporad-
ic vibrations m the stall region were encountered
and are reported. No rotating stall was observed.


NACA TN 3582

EFFECT OF CLIMB TECHNIQUE ON JET-
TRANSPORT NOISE. Warren J. North. January
1956. 19p. diagrs. (NACA TN 3582)

A theoretical investigation of jet-transport climb
technique was made to determine the effect of varia-
tions in engine thrust and airspeed on sound-
pressure levels heard by a ground observer. Re-
duced noise levels will be obtained when climbing on
the steepest flight path consistent with minimum safe
airspeed. Additional noise reduction may be ob-
tained by throttling the engine; however, the addi-
tional benefit accompanying permissible thrust re-
duction is small.


NACA TN 3587

IMPINGEMENT OF WATER DROPLETS ON A
SPHERE. Robert G. Dorsch, Paul G. Saper, and
Charles F. Kadow. November 1955. 29p. diagrs.,
tab. (NACA TN 3587)

Droplet trajectories about a sphere in ideal fluid
flow were calculated. From the calculated droplet
trajectories, the droplet-impingement characteris-
tics of the sphere were determined. Impingement
data and equations for determining the collection ef-
ficiency, the area, and the distribution of impinge-
ment are presented in terms of dimensionless pa-
rameters. The range of flight and atmospheric
conditions covered in the calculations was extended
considerably beyond the range covered by previously
reported calculations for the sphere.


3


NACA TN 3590

INVESTIGATION OF FAR NOISE FIELD OF JETS.
I EFFECT OF NOZZLE SHAPE. Edmund E.
Callaghan and Willard D. Coles. January 1956.
44p. diagrs., photos. (NACA TN 3590)

The noise generation of jets discharging from con-
vergent (circular, square, rectangular, and ellip-
tical), plug, and convergent-divergent nozzles was
investigated. At low jet pressure ratios (less than
2.2) all the nozzles had approximately the same
sound field. At high pressure ratios, all the nozzles
produced noise having discrete-frequency peaks.
Only the convergent-divergent nozzle showed a re-
duction in both amplitude of the discrete-frequency
noise and in total sound power radiated as compared
with ordinary convergent nozzles.





NACA TN 3591

INVESTIGATION OF FAR NOISE FIELD OF JETS.
n COMPARISON OF AIR JETS AND JET ENGINES.
Willard D. Coles and Edmund E. Callaghan.
January 1956. 19p. diagrs., photos.
(NACA TN 3591)

A comparison of the noise generation of air jets and
turbojet engines was made from data obtained from
similar free-field surveys. At jet pressure ratios
below or only slightly above that for choked flow, the
overall sound power was well represented by the
Lighthill parameter, but the sound-power results ob-
tained during afterburner operation were somewhat
low. Directional patterns for overall sound pres-
sures were similar for the engines and air jets.
Air-jet and engine spectral data were dissimilar be-
cause of a dip in the engine-noise spectrum.





NACA TN 3592 ,.

AN OIL-STREAM PHOTOMICROGRAPHIC AERO-
SCOPE FOR OBTAINING CLOUD LIQUID-WATER
CONTENT AND DROPLET SIZE DISTRIBUTIONS
IN FLIGHT. Paul T. Hacker. January 1956. 36p.
diagrs., photos., tabs. (NACA TN 3592)

An airborne cloud aeroscope by which droplet size,
size distribution, and liquid-water content of icing
and nonicing clouds can be determined has been de-
veloped and tested in flight and in wind tunnels with
water sprays. The cloud droplets are continuously
captured in a stream of oil, which is then photo-
graphed. In most cases, droplet size distribution
can be obtained from a single photograph. With the
droplet size distribution known, the liquid-water
content of the cloud can be calculated from the ge-
ometry of the aeroscope, the airspeed, and the oil
flow rate. The aeroscope is described in detail,
and some droplet size distributions and liquid-water
contents obtained during tests are presented.







4


BRITISH REPORTS



N-40505*

Aeronautical Research Council (Gt. Brit.)
THEORY OF THE BROAD-BLADED PROPELLER.
G. I. Ginzel. 1955. 28p. diagrs., tabs.
(ARC CP 208)

The standard propeller theory is that of the lifting
line and therefore valid for narrow blades only.
The present first step towards a theory of the pro-
peller blade as a lifting surface considers, beside
the downwash which induces an inclination of flow,
the downwash derivative and the corresponding in-
duced camber of the streamlines in the special case
of shock free entry of flow at the leading edge. The
result is given in the form of a correction factor to
be applied to the camber ratio of the section derived
by the lifting line theory. The theory of Ludweig
and Ginzel is presented with a modified derivation.
The influence on the camber correction factor of
blade shape, of number of blades, and of circulation
distribution over the radius is shown.


N-40510*

Aeronautical Research Council (Gt. Brit.)
THE MANOEUVRABILITY OF AIRCRAFT IN
CIRCLING FLIGHT. H. L. Price. 1955. 32p.
diagrs. (ARC R & M 2838; ARC 8, 367)

The entry into and recovery from a true banked
horizontal turn executed without sideslip or loss of
height is investigated. The proper continuous co-
ordination of aileron, rudder, and elevator is de-
duced for all stages of the maneuver. It is shown
that the rolling motion is practically unaffected by
the other modes of motion, enabling the kinematics
of the rolling mode to be solved in terms solely of
the applied aileron movement or stick force. The
aileron is regarded as the prime initiator of the
turn, operated in some prechosen manner, and the
elevator and rudder loads are expressed as functions
of the determinable rolling velocity and acceleration.
The loads to trim in the final steady turn are found
as a particular case. Mathematical analysis is
included.


N-40573*

Forest Products Research Lab. (Gt. Brit.)
INVESTIGATIONS INTO GLUES AND GLUING.
PROGRESS REPORT EIGHTY-SEVEN AUGUST
1955. THE COMPARATIVE DURABILITY OF PLY-
WOOD GLUES IN ENGLAND AND IN NIGERIA
(SERIES IV). FIFTH YEAR AND FINAL REPORT.
J. F. S. Carruthers and R. W. Hudson. 9p. tabs.
(Forest Products Research Lab.)

Beech and gaboon plywood made with phenol-,
resorcinol-, melamine-, and fortified and normal
urea-formaldehyde types of adhesives has been
exposed for five years in two English and two
Nigerian environments. The deterioration of all
glues is without practical significance for a normally
heated workshop. In exposed or outdoor sites the
melamine- and fortified and normal urea-
formaldehyde adhesives have either failed or show
significant deterioration.


NACA RESEARCH ABSTRACTS
AND RECLASSIFICATION NOTICE NQ 95

N-40683*

Forest Products Research Lab. (Gt. Brit.)
COMPOSITE WOOD SECTION. TRIALS OF TIM-
BERS FOR PLYWOOD MANUFACTURE. PILLAR-
WOOD CASSIPOUREA ELLIOTII TANGANYIKA.
(48 POUNDS PER CUBIC FOOT AT 15 PER CENT
MOISTURE CONTENT). (PROGRESS REPORT
THIRTY-TWO) October 1955. 7p. tabs. (Forest
Products Research Lab.)

After processing trials this timoer was classed as
being unsuitable for British mills due to its small
diameter, heaviness, variable color, and poor glu-
ing characteristics. Technically the limber is
sound and might be of value in its country of origin.



N-40684*

Forest Products Research Lab. (Gt. Brit.)
COMPOSITE WOOD SECTION. TRIALS OF TIM-
BERS FOR PLYWOOD MANUFACTURE. RED
MERANTI SHOREA PARVIFOLIA BRITISH
NORTH BORNEO. (28 POUNDS PER CUBIC FOOT
AT 15 PER CENT MOISTURE CONTENT). (PROG-
RESS REPORT THIRTY-ONE) October 1955 7p.
tabs. (Forest Products Research Lab.)

As a result of drying, gluing, and compression tests,
this timber is believed to be suitable for use in
British mills for plywood manufacture. Special
handling will be required since the veneer is fragile.



N-40685'

Forest Products Research Lab. (Gt. Brit.)
COMPOSITE WOOD SECTION. TRIALS OF TIM-
BERS FOR PLYWOOD MANUFACTURE. MUHUHU
- BRACHYLAENA HUTCHINISI] TANGANYIKA.
(61 POUNDS PER CUBIC FOOT AT 15 PER CENT
MOISTURE CONTENT). (PROGRESS REPORT
THIRTY) October 1955. 5p. Lab. (Forest Products
Research Lab.)

After processing trials this species was considered
unsuitable for plywood making because of its weight
and the difficulty of conversion to veneer.



N-40686'

Forest Products Research Lab. (Gt. Brit.)
COMPOSITE WOOD SECTION. TRIALS OF TIM-
BERS FOR PLYWOOD MANUFACTURE. SCOTS
PINE PINUS SYLVESTRIS L. HOME GROWN.
(33 POUNDS PER CUBIC FOOT AT 15 PER CENT
MOISTURE CONTENT). DOUGLAS FIR -
PSEUDOTSUGA TAXIFOLIA HOME GROWN. (31
POUNDS PER CUBIC FOOT AT 15 PER CENT
MOISTURE CONTENT). (PROGRESS REPORT
TWENTY-NINE) July 1955. 24p. tabs. (Forest
Products Research Lab.)

Scots pine was found unsatisfactory as plywood due
to its poor gluing characteristics and blistering.
The Douglas fir was classed unsuitable for plywood
making because of knots and the high compression
accompanying the pressure needed to obtain an
acceptable bond.






NACA RESEARCH ABSTRACTS
AND RECLASSIFICATION NOTICE NQ 95 5

N-40687*

Forest Products Research Lab. (Gt. Brit.)
MOISTURE RELATIONS OF COMPOSITE WOOD
PRODUCTS. PROGRESS REPORT TWENTY-EIGHT
- OCTOBER 1955. THE SUPERFICIAL MOVEMENT
OF PLYWOOD. R. A. G. Knight and R. J. Newall.
13p. tabs. (Forest Products Research Lab.)

The superficial movements of plywood of three-ply
construction nith moisture change have been meas-
ured for 69 species. For the two environment
changes, the mean averages of the along- and
across-gram movements for the 69 species were
1 5 percent and 1 4 percent, respectively. The
movement of plywood across the grain was 1 25 that
of veneer or solid wood.






MISCELLANEOUS


N-3074, Suppi 4

INDEX OF NACA TECHNICAL PUBLICATIONS,
JUNE 1954 MAY 1955 1955 viii, 205p.
(NACA)

There is a classified listing of subject categories;
a chronological listing of NACA publications under
each subject category; an alphabetical index to the
subject categories; and an author index.






DECLASSIFIED

NACA RESEARCH REPORTS

NONE.


NACA Langley Field, Va.


























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after that, most of them can be had only on a loan basis. All Wartime Reports are in this category.
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