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C Naio Advisory Committee for Aeronautics-
NO. 87r JeeThAbtetULY-28 ,1954
*AVAILABLE ON LOAN ONLY.
ADDRESS REQUESTS FOR DOCUMENTS TO NACA, 1512 H ST., NW., WASHINGTON ns, D. C., CITING CODE NUMBER ABOVE. EACH TITLE;
THE REPORT TITLE AND AUTHOR.
An analysis is made of a normal-acceleration control
system as applied to a swept-wing fighter airplane.
The results show the response characteristics of the
airplane-autopilot combination. The effects that
changes in altitude and Mach number have on these
response characteristics and the effects of changes
in the parameter settings of the system are investi-
gated. A comparison is also made of the normal-
acceleration system with pitch-attitude, pitching-
velocity, and angle-of-attack systems.
NACA TN 3192
EXPERIMENTAL STRESS ANALYSIS OF
STIFFENED CYLINDERS WITH CUTOUTS. SHEAR
LOAD. Floyd R. Schiechte and Richard Rosecranrs.
July 1954. 87p. diagrs., photo., 13 tabs. (NACA
A cylindrical semimonocoque shell of circular cross
section was mounted as a cantilever and loaded by a
direct shear at the tip. The cylinder was tested with
no cutout, with a rectangular cutout on the tension
side, and with the cutout centered on the neutral axis
on one side of the cylinder. The cutout was succes-
sively enlarged through six sizes varying from 300 to
1300 in circumference and from I and 2 bays in
length. Strain measurements were made with
resistance-type wire strain gages near the cutout on
the stringers, the skin, and the rings for each case.
and the stresses obtained are presented in tables.
NACA TN 3196
LIFT AND PITCHING MOMENT AT SUPERSONIC
SPEEDS DUE TO CONSTANT VERTICAL ACCELER-
ATION FOR THIN SWEPTBACK TAPERED WINGS
WITH STREAMWISE TIPS. SUPERSONIC LEADING
AND TRAILING EDGES. Isabella J. Cole and
Kenneth Margolis. July 1954. 67p. diagrs., 4 tabs.
(NACA TN 3196)
On the basis of linearized time-dependent super-
sonic flow theory, the lift and pitching-moment de-
rivatives due to constant vertical acceleration are
evaluated for a series of thin sweptback tapered
wings with streamwise tips. The analysis is valid.
in general, at those speeds for which the wing leading
and trailing edges are both supersonic. The major
portion of the computational results is presented in
the form of detailed charts covering the practical
range of wing-geometry parameters and Mach number
from which fairly rapid estimates of the derivatives
may be obtained.
CURRENT NACA REPORTS
NACA Rept. 1144
AERODYNAMIC CHARACTERISTICS OF A REFINED
DEEP-STEP PLANING-TAIL FLYING-BOAT HULL
WITH VARIOUS FOREBODY AND AFTERBODY
SHAPES. John M. Riebe and Rodger L. Naeseth.
1953. ii, 19p. diagrs., photos., 8 tabs. (NACA
Rept. 1144. Formerly TN 2489; RM L8F01)
An investigation was made in the Langley 300-mph
7- by 10-foot tunnel to determine the aerodynamic
characteristics of a refined deep-step planing-tail
hull with various forebody and afterbody shapes and,
for comparison, a streamline body simulating the
fuselage of a modern transport airplane. The result
of the tests indicated that the configurations incor-
porating a forebody with a length-beam ratio of 7 had
lower minimum drag coefficients than the configura-
tions incorporating a forebody with length-beam ratio
of 5. The lowest minimum drag coefficients, which
were considerably less than that of a conventional
hull and slightly less than that of a streamline body,
were obtained on the length-beam-ratio-7l forebody,
alone and with round center boom. Drag coefficients
and longitudinal- and lateral-stability parameters
presented include the interference of a 21-percent-
thick support wing.
NACA TM 1372
DROP HAMMER TESTS WITH THREE OLEO STRUT
MODELS AND THREE DIFFERENT SHOCK STRUT
OILS AT LOW TEMPERATURES. (Fallhammer-
versuche mit drei Olfederstrebenmustern and drei
verschiedenen Federstrebenolen bei tiefen
Temperaturen). Kranz. July 1954. 55p. diagrs.'
photos., 10tabs. (NACA TM 1372. Trans. from
Zentrale fiir wissenschaftliches Berichtswesen der
Luftfahrtforschung, Berlin, UM 564, Jan. 17, 1939)
Drop hammer tests with different shock strut models
and shock strut oils were performed at temperatures
ranging to -40 C. The various shock strut models do
not differ essentially regarding their springing and
damping properties at low temperatures; however,
the influence of the different shock strut oils on the
springing properties at low temperatures varies
NACA TN 3191
THEORETICAL INVESTIGATION OF LONGITUDINAL
RESPONSE CHARACTERISTICS OF A SWEPT-WING
FIGHTEICIRPLANE HAVING A NORMAL-
ACCELERATION CONTROL SYSTEM AND A COM-
PARISON WITH OTHER TYPES OF SYSTEMS. Fred
H. Stokes and Charles W. Mathews. July 1954. 50p.
diagrs., tab. (NACA TN 3191)
NACA TN 3203
CONSIDERATIONS ON A LARGE H DAULIC JET
Horne. July 1954. 49p. diagrs., photos., tab.
(NACA TN 3203. Formerly RM L51B27)
A survey of various types of catapults, which has
been made in connection with the problem of
ac ea tn c a lr ge fr 0,0 sb ta on g a trc
various design problems of this type are treated.
Equati ns are given for calculat ag th dperfrfm nce
given to the physical conditions affecting the jet flow.
Design procedures are presented for the jet nozzle
and for the bucket on the car which receives the jet
and imparts thrust to the car. The expected propul-
sive efficiency of the jet catapult is given and the ef~
feet of a side wind on the jet trajectory is calculated.
NACA TN 3205
THEORETICAL INVESTIGATION AT SUBSONIC
SPEEDS OF THE FLOW AHEAD OF A SLENDER
INCLINED PARABOLIC-ARC BODY OF REVOLU-
TION AND CORRE LATION WITH EXPERIMENTAL
DATA OBTAINED AT LOW SPEEDS. William Letko
and Edward C. B. Danforth, III. July 1954. 56p.
diagrs. (NACA TN 3205)
Approximate formulas, based on subsonic linearized
theory, are derived for the static-pressure incre-
ment and flow inclination ahead of slender inclined
parabolic-are bodies of revolution at subsonic
speeds. Charts are presented from which these
quantities can be estimated. Some comparisons with
experimental data obtained for a Mach number of
0. 21 are also presented. Consideration is given to
the induced effects of the wing and mounting boom on
NACA TN 3208
HEAT, MASS, AND MOMENTUM TRANSFER FOR
FLOW OVER A FLAT PLATE WITH BLOWING OR
SUCTION. H. S. Mickley, R. C. Ross, A. L. Squyers
and W. E. Stewart, Massachusetts Institute of
Technology. July 1954. ii, 149p. diagrs., photos.,
9 tabs. (NACA TN 3208)
The effect on the boundary layer of sucking or blow-
ing air through a porous flat plate into or out of a
main air stream flowing parallel to the plate was
studied theoretically and experimentally. Laminar-
boundary-layer theory was used to calculate transfer
coefficients and velocity, temperature, and concentra-
tion profiles in laminar, zero Euler number flow
under certain restricted mass transfer conditions and
for a range of Prandt1 or Schmidt numbers. For tur-
bulent flow film theory was used to predice the effect
of mass transfer on friction, heat, and mass transfer
coefficients. Experimental measurements of velocity
and temperature profiles and of friction and heat
transfer coefficients were carried out over a range
of flow conditions.
RESEARCH ABSTRACTS NO. 67
NACA TN 3225
PE SURMENSRAIBLUSTON0 O UBEWEDGE
PROFILE AT MACH NUMBERS NEAR SHOCK
ATTACHMENT. Walter G. Vincenti, Duane W. Dugan
and E. Ray Phelps. July 1954. 43p. diagrs.
(NACA TN 3225)
sni s eeds1 ofe prsue dsrbton o ble-
(1.221) for bow-wave attachment at zero angle of
with tei fi d s ofte r noic dm -im rrbeadnce
NACA TN 3255
SHOCK-TURBULENCE INTERACTION AND THE
GENERATION O1F NOISE. H. S. Ribner. July 1954.
60p. diagrs., tab. (NACA TN 3255)
Interaction of convected field of turbulence with shock
wave is analyzed to yield modified turbulence, entro-
py spottiness, and noise generated downstream of the
shock. Analysis is generalization of single-spectrum-
wave treatment of TN 2864. Formulas for spectra
and correlations are obtained. Numerical calcula-
tions yield curves of rms velocity components, tem-
perature, pressure, and noise in db against Mach
number for M = 1 to *; both isotropic and strongly
axisymmetric (lateral/longitudinal = 36/1) initial
turbulence are treated. In either case, turbulence of
0.1 percent longitudinal component generates about
120 dbs of noise.
NACA TN 3256
EXPERIMENTAL INVESTIGATION OF TEMPERA-
TURE RECOVERY FACTORS ON A 100 CONE AT
ANGLE OF ATTACK AT A MACH NUMBER OF 3.12.
John R. Jack and Barry Moskowitz. July 1954. 15p.
diagrs. (NACA TN 3256)
At angles of attack from 00 to 100 over the Reynolds
number range (1.5 to 8 x 106), an increase in angle of
attack increased the equilibrium surface tempera-
tures in the laminar and turbulent flow regions. The
equilibrium surface temperatures in regions of prob-
abe cross-flow se Iratmon were in tim saomet rnge
ward surface, local recovery factors in the fully
laminar and turbulent regions were not significantly
affected by changes in angle of attack.
Royal Aircraft Establishment (Gt. Brit.)
THE CHANGE IN INFLUENCE COEFFICIENTS
CAUSED BY A CHANGE OF DATUM. D. Williams,
April 1954. 8p. diagrs. (RAE Tech.Note Structures
A metdo fs dcjnbe fr trasfo n t set of in-
given datum into an equivalent set relative to a
RESEARCH ABSTRACTS NO.,7
Royal Aircraft Establishment (Gt. Brit.)
A METHOD FOR CALIBRATING A WIND TUNNEL
REAR STING BALANCE. J. R. Anderson. March
1954. 14p. diagrs., tab. (RAE Tech. Note Aero
A method is described for calibrating a wind-tunnel
balance consisting of a sting support bearing strain
gages. The form of calibration obtained is essen-
tially suitable for the automatic computing of wind-
tunnel results. The technique of static loading of
the balance is discussed, and an appendix contains
practical notes on matrix inversion.
Nat. Gas Turbine Establishment (Gt. Brit.)
AN APPLICATION OF THE CAPACITY PROBE
METHOD TO THE MEASUREMENT OF ROTOR
BLADE TIP DEFLECTIONS IN AN AXIAL COM-
PRESSOR. R. Chaplin. December 1953. 35p.
diagrs., photos. (NGTE Memo. M. 199)
An application to the first rotor stage of an axial
compressor, or the capacity probe method of meas-
uring blade tip deflections is described. Results
obtained from strain gages on the same stage are in-
cluded. Results from the capacity probe method
were not satisfactory and it is suggested that the
standards of stability required by this method were
not practicable in this instance.
Royal Aircraft Establishment (Gt. Brit.)
CORROSION OF STAINLESS STEEL AND ALUMINI-
UM ALLOYS IN CONTACT WITH TITANIUM. C.
Braithwaite. February 1954. 18p. photos., 2tabs.
(RAE Tech. Note Met. 192)
Titanium samples consisting of 1-inch diameter
d acd hncnactna witn hti meses hee dndb a nu
alloys and exposed to the intermittent seawater spray
test for 1 year. Test results and recommendations
for corrosion prevention of these joints are given.
Forest Products Research Lab. (Gt. Brit.)
INVESTIGATIONS INTO GLUES AND GLUING*
PROGRESS REPORT SEVENTY-SIX MARCH 1954.
DURABILITY TESTS ON PLYWOOD ADHESIVES -
SERIESTI. ANALYSIS AFTER SEVEN AND A HALF
YEARS. R. A. G. Knight, R. J. Newall and J. E.
Grosert. 9p. 4 tabs. (Forest Products Research
Lab. Supersedes Progress reports 44, 46, 46 (add. )
This report analyzes the behavior of a range of ad-
hesives used in beech plywood exp~osed to four natural
conditions: storage in a normally heated workshop;
exposure to the weather on racks facing south In an
open field; storage in an open-sided shed and momen-
tarily dipped in water once a month; and submersion
in fresh water tanks standing in the open. The ad-
hesives include a number of phenolic and resorcinol
resins, one experimental melamine, fortified and
normal ureas, casein and animal glues and sodium
ON THE MAGNUS EFFECT ACCORDING TO THE
ASYMPTOTIC HYDRODYNAMIC THEORY. (Uboer
den Magnuseffekt nach der Asymptotischen
Hydrodynamischen Theorie). Torstetn Gustafson.
June 1954. ii, 93p. diagrs., photos. (Trans. from
Hakan Ohtssons Buchdruckerei, Lund, 1933)
A comparison of the theoretically and experimentally
determined values of pressure, drag. and lift on a
rlsting cylinder in fluid flow gives information on
how far the asymptotic flow theory is capable of
reproducing the characteristic properties of the
actual flow in the case of small friction. The pres-
sure values as well as the lift coefficients agree with
experiments. For a prescribed flow in the case of
small friction the flow process can be represented by
determination of the wake form and formation of the
corresponding potential expressions.
Iowa State College. ROLE OF TRIPLE COLLISIONS
IN EXCITATION OF MOLECULAR VIBRATIONS.
Richard Alden Walkrer. 1952. vii, 132p. diagrs,,
photos., 8 tabs. (Iowa State College)
An experimental program has been initiated to study
thermal relaxation in gas mixtures. The major goal
of this work is to reach a better understanding of the
perplexing trace catalysts problem. The initial
phase ofo heepo I am repored ms bhi pape h t oben
excitation in mixtres.
TESTS ON A FLAT PLATE IN A UNIFORM AIR-
STREAM, REGARDING THE INFLUENCE OF
ROUGHNESS ON THE TRANSITION FROM LAMINAR
TO TURBULENT FLOW. (Versuche an einer
parallel angestromten ebenen Platte uber den
Rauhigkeitseinfluss auf den Umschlag laminar,
turbulent). Horst Holstein. April 1954. 16p.
diagrs. (Trans. from Zentrale fur
wissenschaftliches Berichtswesen der Luftfahrt-
forschung, Berlin, UM 3110, June 8, 1944)
A study is made of the maximum roughness that a
surface may have without causing a significant
forward-shifting of the transition point. Results
show that in the case of small roughness the critical
R ynolds number does nt depend to a very high
NACA-Langley 7-28-54 4M
UNIVERITY OF LORID
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