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Natioan- Advisory Committee For Aeronautics
NO. 81 t. 5 APRIL 20, 19
.CU R 'NT NACA .REPORTS
)TACA TM 1 -
S: APPARATUS FO1- MEAS MENTS OF TIME AND
-SPACE CORRELATION. (Appareil de Mesures de la
Correlation Dans le Temps et L'Espace). A. Favre,
J. Gaviglio and R. Dumas. (Presented at eighth In-
ternational Congress for Theoretical and Applie --
Mechanics, Istanbul, Aug., 1952) April 1955. 2 .
diagrs., photos. (NACA TM 1371. Trans. from a a
p echbrche Aeronautique, no.31, Jan.-Feb., 1953,
A brief review is made of improvements to an ex-
Sperimental apparatus for lime and space correlation
designed for study of turbulence. Included is a des-
cription of the control of the measurements and a
few particular applications. i
NAFA TM 1387
THEORY OF REVERSIBLE AND NONREVERSIB EI
C. .IlACKS IN SOLIDS. (Teoriya obratimykh i
ijieobratimykh treshchin v tverdykh telakh). Y. I.
S Frenkel. April 1955. 14p. diagrs. (NACA
TM 1387. Trans. from Zhurnal Tekhnicheskoi
Fiziki, v. 22, no. 11, Nov., 1952, p. 1857-1866)
The Griffith crack theory is reviewed and certain
S shortcomings of this theory are discussed. A new
Slcription for the shape of a crack is given which
S. ke..i s into account the atomic structure of material.
Through consideration of the total energy of the
system and the shape of the crack, expressions for
cck behavior are derived which are considered to
e, .:.. edy the defects of the Griffith theory.
S NACA TN 3216
COOPERATIVE INVESTIGATION OF RELATIONSHIP
t EEN STATIC AND FATIGUE PROPERTIES
S HT N-155 ALLOY AT ELEVATED
"ERATURES. NACA Subcommittee on Heat-
lisisting Materials. April 1955. 92p. diagrs.,
photos., 13 tabs. (NACA TN 3216)
Extensive data are given relating properties of N-155
alloy under static, combined static and dynamic, and
completely reversed dynamic stress conditions.
Time periods for fracture ranged from 50 to 500
hours at room temperature, 1,0000, 1,2000, 1,3500,
and 1,5000 F. The work was on a cooperative basis
to help clarify the principles governing load-carrying
ability of heat-resistant alloys at temperatures and
conditions where both creep and fatigue can occur
simultaneously. In view of the uncertainty in inter-
preting results of various types of fatigue tests,
duplicate data were obtained from as many types of
fatigue testingmachines as could be arranged.
NACA TN 3270
EFFECT OF DISSOCIATION ON THERMODYNAMIC
PROPERTIES OF PURE DIATOMIC GASES. Harold
W. Woolley, National Bureau of Standards. April
1955. 19p. diagrs., tab. (NACA TN 3270)
-.-Agraphical method is described by which the enthalpy,
entropy, and compressibility factor for the equilib-
rium mixture of atoms and diatomic molecules for
pure gaseous elements may be obtained and shown
f. er-any dissociating element for which the necessary
data exist. ReSults jre given for hydrogen, oxygen,
and pil-ogen.",The efect of dissociation on the heat
c.... cpa .jV !did briefly.
R NULAR CORROSION OF HIGH-PURITY
'ALU IN HYDROCHLORIC ACID. n -
GRA4-'pUNDARY SEGREGATION OF IMPURITY
ATOMS. M. Metzger and J. Intrater, Columbia
U$ er'ty. April 1955. 33p. diagrs., 4 tabs.
=-_NACA TN 3282)
-- The variation in the rate of intergranular corrosion
of single-phase high-purity aluminum in 20 percent
hydrochloric acid as a function of iron content and
final-annealing temperature is attributed to the
segregation to atomic sites in the grain-boundary
region of iron and possibly other impurity atoms.
The experimental results are analyzed by reference
to a distribution function, obtained by statistical
mechanical methods, which gives the equilibrium
fraction of certain sites in the boundary which are
occupied by solute atoms in terms of the interaction
energy for the segregation of the solute atoms at
NACA TN 3326
THE COMPRESSIBLE LAMINAR BOUNDARYLAYER
WITH HEAT TRANSFER AND ARBITRARY PRES-
SURE GRADIENT. Clarence B. Cohen and Eli
Reshotko. April 1955. 43p. diagrs., 2 tabs. (NACA
An approximate method for the calculation of the
compressible laminar boundary layer with heat
transfer and arbitrary pressure gradient, based on
Thwaites' correlation concept, is presented. With
the definition of dimensionless shear and heat-
transfer parameters and an assumed correlation of
these parameters in terms of a momentum param-
eter, a complete system of relations for calculating
skin-friction and heat-transfer results. Knowledge
of velocity or temperature profiles is not necessary
in using this calculation method. When the method
is applied to a convergent-divergent, axially sym-
metric rocket nozzle, it shows that high rates of
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c. L", rSv
heat transfer are obtained at the initial stagnation
point and at the throat of the nozzle. Also indicated
are negative displacement thicknesses in the con-
vergent portion of the nozzle; these occur because of
the high density within the lower portions of the
cooled boundary layer.
NACA TN 3351
PLASTIC DEFORMATION OF ALUMINUM SINGLE
CRYSTALS AT ELEVATED TEMPERATURES.
R. D. Johnson, A. P. Young and A. D. Schwope,
Battelle Memorial Institute. April 1955. 76p.
diagrs., photos., 3 tabs. (NACA TN 3351)
A study was made of plastic deformation of aluminum
single crystals over a wide range of temperatures.
Results are presented of constant-stress creep tests,
constant-load-rate tests, and constant-load creep
tests. The effect of crystal orientation on the oper-
atliv slip system was determined. The effect of
small amounts of prestrairung was studied and two
high-resolution X-ray techniques were used to
detect and follow the strain. Light and electron
microscopy were used to study the complex nature
of slip bands and kink bands on specimens deformed
at elevated temperatures.
NACA TN 3370
A SIMPLIFIED METHOD FOR CALCULATING
AEROELASTIC EFFECTS ON THE ROLL OF AIR-
CRAFT. John M. Hedgepeth, Paul G. Waner, Jr.
and Robert J. Kell. March 1955. 26p. diagrs..
4 tabs. (NACA TN 3370)
An approximate linearized lifting-surface theory is
used in conjunction with structural influence coef-
ficients to formulate a method for analyzing the aero-
elastic behavior in roll of an aircraft. Rolling ef-
fectiveness and aileron-reversal speed are computed
by the use of a Galerkin-type procedure. Results
obtained for two example configurations by using this
method are compared with the results obtained by
using the more refined method of NACA TN 3067.
NACA TN 3373
THEORETICAL CALCULATIONS OF THE PRES-
SURES, FORCES, AND MOMENTS DUE TO
VARIOUS LATERAL MOTIONS ACTING ON THIN
ISOLATED VERTICAL TAILS WITH SUPERSONIC
LEADING AND TRAILING EDGES. Kenneth
Margolis. March 1955. 43p. diagrs., 10 tabs.
(NACA TN 3373)
Expressions based on linearized thin-airfoil theory
for supersonic speeds are derived for the velocity
potentials and pressure distributions due to various
lateral motions for a family of thin isolated vertical
tails with arbitrary sweepback and taper ratio.
Motions treated are steady rolling, steady yawing,
constant sideslip, and constant lateral acceleration.
For the particular cases of half-delta and rectan-
gular vertical tails, forces and moments expressed
in the form of stability derivatives are also derived
and presented in simple charts. All results are, in
general, apphcable at those supersonic speeds for
which both the tail leading and trailing edges are
supersonic. End-plate effects for several of the
derivatives are also considered.
RESEARCH ABSTRACTS NO. 81
NACA TN 3376
THE EFFECT OF CONTROL STIFFNESS AND FOR-
WARD SPEED ON THE FLUTTER OF A 1/10-SCALE
DYNAMIC MODEL OF A TWO-BLADE JET-DRIVEN
HELICOPTER ROTOR. George W. Brooks and
Maurice A. Sylvester. April 1955. 38p. diagrs.,
photo., 3 tabs. (NACA TN 3376)
Some tests have been made with a 1/10-scale dynam-
ic model of a two-blade jet-drive helicopter to study
the effects of blade-pitch-control stiffness and tip-
speed ratio on the rotor blade flutter characteristics.
The results showed that the flutter speed of the model
blades was increased as the blade-pitch-control stiff-
ness was increased and indicated that the structural
blade modes of primary importance with respect to
flutter were the first torsion mode and the flapping
mode. The rotor speed at flutter was reduced
slightly as the tip-speed ratio was increased from
hovering to forward flight.
NACA TN 3383
INVESTIGATION OF THE TURBULENT BOUNDARY
LAYER ON A YAWED FLAT PLATE. Harry
Ashkenas and Frederick R. Riddell, Cornell
University. April 1955. 57p. diagrs., photos.
(NACA TN 3383)
Experiments carried out on three flat plates yawed
00, 300, and 450 with artificially fixed transition in a
low-speed, low-turbulence tunnel are described.
The effects of yaw on the velocity profile and on the
direction of flow near the plate are found to be small.
The boundary-layer displacement thickness on a
yawed plate is found to grow in the streamwise di-
rection at a rate slightly greater than it does on the
unyawed plate; this is in contrast with the Laminar
case where the "independence principle" discovered
by Prandtl and others leads to a substantially reduced
rate of growth on yawed plates.
NACA TN 3392
TWO MINIATURE TEMPERATURE RECORDERS
FOR FLIGHT USE. John V. Foster. April 1955.
13p. diagrs., photos. (NACA TN 3392)
Descriptions are given for two types of temperature
recorders suitable for use with thermocouples on
fighter-type aircraft. One is an electromechanical
self-balancing potentiometer type; the other uses
electronic feedback to achieve fast balance.
NACA TN 3393
AN EXPERIMENTAL INVESTIGATION OF THE
BASE PRESSURE CHARACTERISTICS OF NON-
LIFTING BODIES OF REVOLUTION AT MACH
NUMBERS FROM 2.73 TO 4.98. John O. Reller, Jr.
and Frank M. Hamaker. March 1955. 45p. diagrs.,
photos. (NACA TN 3393. Formerly RM A52E20)
Base pressure characteristics of related nonlifting
bodies of revolution were investigated at free-stream
Mach numbers from 2.73 to 4.98 and Reynolds num-
bers from 0.6 x 106 to 8.8 x 106. The basic body
shape was a 10-caliber tangent ogive with a cylind-
rical alterbody. The variation of base pressure co-
efficient with free-stream Mach number and
RESEARCH ABSTRACTS NO. 81
Reynolds number was determined for laminar-,
transitional-, and turbulent-boundary-layer flow.
Some effects of body fineness ratio, nose-profile
shape, and afterbody shape (boattail) were also in-
cluded in the investigation.
NACA TN 3420
HYDRODYNAMIC TARES AND INTERFERENCE
EFFECTS FOR A 12-PERCENT-THICK SURFACE-
PIERCING STRUT AND AN ASPECT-RATIO-0.25
LIFTING SURFACE. John A. Ramsen and Victor L.
Vaughan, Jr. April 1955. 20p. diagrs. (NACA
Results are presented from an investigation of the
hydrodynamic tares and interference acting on an
NACA 661-012 airfoil-section surface-piercing strut
and.an aspect-ratio-0.25 modified-flat-plate rectan-
gular lifting surface. The interference of the strut
on the lifting surface was negligible except at very
shallow depths, where it increased the lift and
pitching moment slightly. Strut-tare effects were
appreciable only on drag, where section-drag coef-
ficients showed good agreement with data from pre-
vious tank and wind-tunnel tests. The surface-
intersection drag coefficients were constant above
the critical wave speed and showed fairly good
agreement with wave-drag theory below the critical
NACA TN 3426
AN EXPERIMENTAL STUDY OF ORIFICE COEF-
FICIENTS, INTERNAL STRUT PRESSURES, AND
LOADS ON A SMALL OLEO-PNEUMATIC SHOCK
STRUT. James H. Walls. April 1955. 23p.
diagrs., photos. (NACA TN 3426)
Measurements of shock-strut internal pressures,
telescoping velocity, and strut stroke were made
during drop tests of a small oleo-pneumatic landing
gear to determine the characteristics of the orifice
and to show the relationships between internal strut
pressures and the overall loads developed by the
strut. The variation of the orifice coefficient with
telescoping velocity and strut stroke is presented.
Strut forces determined from internal-pressure
measurements are compared with forces measured
by an external dynamometer. Strut forces calculated
from measured telescoping velocity and stroke time
histories are evaluated, a constant orifice coefficient
and isothermal air compression being assumed.
NACA TN 3428
GROUND-SIMULATOR STUDY OF THE EFFECTS
OF STICK FORCE AND DISPLACEMENT ON
TRACKING PERFORMANCE. Stanley Faber.
April 1955. 21p. diagrs., photos. (NACA TN 3428)
Tests were performed on a ground simulator with
one degree of freedom, pitch, to determine the de-
sired magnitude of the control-stick forces and dis-
placements in relation to the performance of a track-
ing task. The dynamics of the simulated airplane
were typical of those of current fighters operating at
low altitudes and at subsonic speeds and having an
undamped natural frequency of 1/2 cycle per second
and a damping ratio of approximately 0.8.
NACA TN 3429
STATIC STABILITY OF FUSELAGES HAVING A
RELATIVELY FLAT CROSS SECTION. Willam R.
Bates. March 1955. 29p. diagrs., tab. (NACA
TN 3429. Formerly RM L9106a)
The subject investigation contains results of force
tests and flow surveys made in the Langley free-
flight tunnel to determine the static stability char-
acteristics of several fuselages having a relatively
flat cross section and a high fineness ratio.
NACA TN 3430
ON SLENDER DELTA WINGS WITH LEADING-EDGE
SEPARATION. Clinton E. Brown and William H.
Michael, Jr. April 1955. 27p. diagrs. (NACA
The slender-body approximation of linearized com-
pressible flow is applied to the problem of a delta
wing in which flow separation occurs at the leading
edges. The vortex sheets found in the real flow are
approximated by concentrated vortices with feeding
lattices, and an adaptation of Kelvin's theorem is
applied to simulate the force-free nature of the vor-
tex sheet. Computed pressure distributions and
span loadings are presented, and the theoretical lift
results are compared with the results of simple
force tests made at a Mach number of 1.9.
NACA TN 3431
AN ANALYSIS OF THE STABILITY AND ULTIMATE
COMPRESSIVE STRENGTH OF SHORT SHEET-
STRINGER PANELS WITH SPECIAL REFERENCE
TO THE INFLUENCE OF RIVETED CONNECTION
BETWEEN SHEET AND STRINGER. Joseph W.
Semonian and James P. Peterson. March 1955.
49p. diagrs., tab. (NACA TN 3431)
A method of strength analysis of short sheet-stringer
panels subjected to compression is presented which
takes into account the effect that the riveted attach-
ments between the plate and the stiffeners have on
the strength of panels. An analysis of experimental
data shows that panel strength is highly influenced by
rivet pitch, diameter, and location and that the
degree of influence for a given riveting depends on
the panel configuration and panel material.
NACA TN 3432
CIRCUMFERENTIAL DISTRIBUTION OF
RISE AT ONE RADIAL STATION OF A TWIN-
ENGINE TRANSPORT AIRPLANE. A. W. Vogeley
and H. A. Hart. April 1955. 24p. diagrs., photos.
(NACA TN 3432)
Flight tests on a twin-engine transport airplane have
been made to determine the effects of fuselage-
nacelle interference on the circumferential distribu-
tion of the rise in total pressure behind the propel-
lers. The effects of this flow interference on the
operation of a simple propeller-thrust indicator,
which samples the total-pressure rise at two dia-
metrically opposed points in the slipstream (to
counteract the effects of variations in angles of pitch
and yaw), have been investigated.
NACA TN 3434
A STUDY OF NORMAL ACCELERATIONS AND
OPERATING CONDITIONS EXPERIENCED BY
HELICOPTERS IN COMMERCIAL AND MILITARY
OPERATIONS. Marlin E. Hazen. April 1955. 34p.
diagrs., photos., 5 tabs. (NACA TN 3434)
An analysis is presented of the normal accelerations
and operating conditions encountered by two different
airmail helicopters and a military pilot-training
helicopter. Tables and graphs are used to illustrate
the effect of operating conditions on acceleration
levels, and a summary of all NACA helicopter VGH
data analyzed to date is included.
NACA TN 3446
EFFECT OF AMMONIA ADDITION ON LIMITS OF
FLAME PROPAGATION FOR ISOOCTANE-AIR
MIXTURES AT REDUCED PRESSURES AND ELE-
VATED TEMPERATURES. Cleveland O'Neal, Jr.
April 1955. 32p. diagrs., 3 tabs. (NACA TN 3446)
Limits were determined for isooctane, ammonia,
and mixtures of these two fuels with air at pressures
up to 400 mm Hg and temperatures from 600 to 4000
C. In the ternary mixtures, NH3-air weight ratios
were 0. 020 and 0. 039. For all mixtures, the flam-
mable region (rich minus lean limit equivalence
ratio) broadened as the temperature was raised. The
flammable region of isooctane was roughly three
times that of ammonia. However, small additions of
ammonia to isooctane broadened the flammable
range up to an NH3-air ratio of about 0.02; further
additions narrowed the range. Added ammonia was
completely consumed in lean mixtures; in rich mix-
tures about half of the ammonia was unburned.
NACA TN 3447
ANALYTIC DETERMINATION OF THE DISCHARGE
COEFFICIENTS OF FLOW NOZZLES. Frederick S.
Simmons. April 1955. 15p. diagrs. (NACA
An analytic expression for the discharge coefficient
of flow nozzles is obtained by integration of an
approximation for the velocity profile through the
cross section of the nozzle. This expression shows
the discharge coefficient to be a function of the
Reynolds number and the geometry of the nozzle and
agrees well with published experimental data for
Reynolds numbers between 104 and 106.
NACA TN 3496
FLIGHT TESTING BY RADIO REMOTE CONTROL -
FLIGHT EVALUATION OF A BEEP-CONTROL
SYSTEM. Howard L. Turner, John S. White and
Rudolph D. Van Dyke, Jr. March 1955. 55p.
diagrs., photos., tab. (NACA TN 3496. Formerly
A comparison between manual control and remote
control showed that a beep-type, radio-remote-
control system was, in general, a satisfactory
means of control for conducting standard handing-
quality flight tests. The dynamic characteristics of
the airplane-autopilot combination and the selection
of the proper parameter adjustments are discussed.
RESEARCH ABSTRACTS NO. 81
Aeronautical Research Council (Gt. Brit.)
DIFFUSION OF ANTISYMMETRICAL LOADS INTO,
AND BENDING UNDER, TRANSVERSE LOADS OF
PARALLEL STIFFENED PANELS. J. H. Argyris.
1954. 52p. diagrs. (ARC R 6 M 2822. Formerly
ARC 9662; Strut 1037)
The purpose of this paper is to present the general
theory of diffusion of antisymmetrical concentrated
end loads and edge loads into parallel stiffened
panels, including the theory of bending of a parallel
stiffened panel under arbitrary transverse loads.
By combining the results of this paper with the re-
sults on diffusion of symmetrical loads given in
R i M 1969 and R & M 2038 or in Appendix I to this
paper, it is possible to analyze the diffusion in a
parallel panel under any arbitrary load or edge
Aeronautical Research Council (Gt. Brit.)
THE DETERMINATION OF THE PRESSURE DIS-
TRIBUTION OVER AN AEROFOIL SURFACE BY
MEANS OF AN ELECTRICAL POTENTIAL
ANALYSER. S. C. Redshaw. 1954. 40p. diagrs.,
photos., tabs. (ARC R .- M 2915; ARC 15,733.
Formerly Boulton Paul Aircraft Ltd. Tech. Rept. 101)
The potential flow, both with and without circulation
around several thin wings has been studied by means
of a three-dimensional potential analyzer. It is
shown that, by using the normal assumptions made
in the exercise of the linear perturbation theory, it
is possible to obtain the pressure distribution for
small angles of attack, as well as the slope of the
lift-incidence curve, easily and rapidly. Experi-
ments are also described in which it was attempted
to remove the effect of boundary restraint in a man-
ner analogous to that used in a flexible walled wind
Royal Aircraft Establishment (Gt. Brit.)
BOUNDARY LAYER MEASUREMENTS ON 100 AND
200 CONES AT M = 2.45 AND ZERO HEAT TRANS-
FER. E. V. Davies and J. R. Cooke. November
1954. 62p. diagrs., photos., 2 tabs. (RAE Tech.
Note Aero 2314)
Transition from laminar to turbulent flow occurred
between 4 and 6 in. from the tip of the 100 cone at
Reynolds number between 106 and 1.4 x 106; the
layer on the 200 cone was laminar over its entire
length of 6 in. (Reynolds number = 1.4 x 106).
Results agree well with the flat plate solution of
Monaghan transformed by the theoretical cone-flat
plate relations of Hantzsche and Wendt, and Mangler.
The data for the turbulent boundary layer were
obtained from the 100 cone and comparison with flat
plate data indicates that the cone-flat plate relation
is within 6 percent of an empirical relation analogous
to the F laminar boundary layer factor.
RESEARCH ABSTRACTS NO.81
Royal Aircraft Establishment (Gt. Brt.)
A FLIGHT INVESTIGATION OF THE WAKE BEHIND
A METEOR AIRCRAFT, WITH SOME THEORETICAL
ANALYSIS. D. R. Andrews. December 1954. 38p.
diagrs., photos., tab. (RAE Tech. Note Aero 2283)
The jet velocity falls to a negligible value by 200-300
feet behind the jet exit. Major disturbances behind
an aircraft are due to the trailing vortices and these
decay only slowly. Tests with a Vampire flying in
the wake show that the strength of these vortices has
fallen to about half its initial value by 8000 feet
behind the aircraft. Theory and flight tests show
that the rolling moment imposed on a tracking air-
craft constitutes the most severe disturbance from
these vortices, and in some cases this rolling
moment can be large enough to overpower the aileron
control of the tracking aircraft.
Royal Aircraft Establishment (Gt. Brit.)
CURRENT INTERRUPTION OF D.C. CIRCUITS IN
AIR AT LOW PRESSURES, WITH SPECIAL REFER-
ENCE TO THE ARC CHARACTERISTIC BETWEEN
SILVER ELECTRODES. A. H. M. Arnold and L. H.
Ford. July 1954. 34p. diagrs., 11 tabs. (RAE
Measurements have been made of the voltage and
current in d-c arcs over a range of air pressures
using silver, copper, and tungsten electrodes. The
investigation has shown that although the arc charac-
teristic at low pressures is less favorable for break-
ing large currents than it is at atmospheric pressure,
comparable switch performance may usually be ob-
tained either by an increase of gap length, or by an
increase in the number of series breaks. Simple
empirical relationships for the arc characteristics
based on the experimental data obtained are given
for silver and tungsten electrodes: tests on the
interrupting capacity of switches gave results which
were in reasonable agreement with predictions made
from these empirical formulas.
Royal Aircraft Establishment (Gt. Brit.)
SOME EXPERIMENTS ON RATES OF QUENCHING.
F. J. Bradshaw and S. Pearson. October 1954.
lip. diagrs. (RAE Tech.Note Met.203)
Experiments are described on the quenching rates
of 6.4 mm diameter cylindrical specimens in water
at various temperatures. Similar work is described
using cylinders and wires (1.2 to 0.3 mm) quenched
in liquids held at temperatures below 00 C. Appro-
priate mean values of surface heat transfer coeffi-
cients are deduced.
Royal Aircraft Establishment (Gt. Brit.)
28 S. W. G. TITANIUM SHEETING FOR FIREPROOF
BULKHEADS. J. T. Ballett. September 1954. 7p.
photos., 2 tabs. (RAE Tech. Note Met. 202)
Tensile and bend tests were made on 28 S.W. G
(0.015 in.) Ti 75A titanium sheet in the annealed
condition and also after exposure in a furnace at
10000 C for 5 minutes. Exposure tests were also
carried out using two different types of torch flames.
The results showed that the heating to 10000 C
increased the tensile strength of the material by
about 20 percent to 49 tons/sq in., with an accom-
panying reduction in elongation from 28 percent to
SELECTIVITY IN THE FORMATION OF FATIGUE
CRACKS DURING THE WORKING OF STEEL IN A
CORROSIVE MEDIUM; AND ADSORPTIVE BEGIN-
NING OF THE CORROSIVE FATIGUE OF METALS.
(Pro Vibirnist' v Utvorenni Trishchin Vtomi pri
Roboti Stall u Koroziynomu Seredovishchi, and
Adsorbtsiinii Pochatok Koroziinoi Vtomi Metaliv).
G. V. Karpenko. lip. diagrs., photos. (Trans.
from Akademiia Nauk URSR, Kiev, Dopovidi, no. 2,
1951, p. 112-119)
In part I, steel was tested under reversed torsion in
air and aerated water. Transcrystalline cracks
perpendicular to the maximum tensile stress were
observed. All cracks were found to be normal to
the surface. In part II, the effects of an actively
corrosive media as well as a superficially corrosive
one were considered.
Univ. of Calif., Berkeley. Institute of Engineering
Research. A MACH 3.106 TWO-DIMENSIONAL
ADJUSTABLE NOZZLE FOR LOW DENSITY FLOW
(NO. 10 NOZZLE). L. Talbot. February 18, 1954.
(iii), 29p. diagrs., photos., 3 tabs. (Univ. of Calif.,
Berkeley. Institute of Engineering Research.
Following the results of tests conducted in a small
wind tunnel, a Mach 3.106 adjustable throat two-
dimensional nozzle was designed for the No. 3 Wind
Tunnel of the Low Pressures Project. The nozzle
measured 11.05 in. from throat to exit and, includ-
ing boundary-layer corrections, had exit dimensions
of 3.899 in. x 4.116 in. Test section Mach numbers
from 2.50 to 6.53 were produced by varying the noz-
zle throat height. The uniform flow region decreas-
ed with increased Mach number; at the highest Mach
number the nozzle was completely filled with bound-
Polytechnic Institute of Brooklyn. THE NON-
LINEAR DEFLECTION OF INFINITE STRIP PLATES.
F. S. Shaw, F. Pohle and N. Perrone. June 1953.
16p. diagrs., tab. (Polytechnic Institute of Brooklyn.
By expressing the von Karmin plate theory entirely
in terms of displacements, there result three simul-
taneous nonlinear governing equations. These are
not readily soluble. If, however, the plate is taken
to be an infinite strip, and the loading to vary on in
the finite direction, solutions can be obtained for a
variety of loading cases. This restricted class of
problems is discussed here, and the solution for the
case of uniform loading is considered in all detail.
Polytechruc Institute of Brooklyn. THE NON-
LINEAR DEFLECTION OF AN INFINITE STRIP
MEMBRANE. N. Perrone, F. Pohle and F. S. Shaw.
April 1953. 13p. diagr. (Polytechnic Institute of
Brooklyn. PIBAL Rept. 219)
The problem of the nonlinear deflection of a mem-
brane having the shape of an infinite strip is consid-
ered. By setting up the problem in terms of dis-
placement components, it is shown that it is possible
to obtain exact, simple, closed form solutions for a
variety of loading cases which are subject to the
restriction that variation is in the finite direction
Univ. of Okla. Research Institute. FLAME STA-
BILIZATION RESULTING FROM CYCLONIC FLOW
IN MIXTURES OF NATURAL GAS AND AIR. Lyle F.
Albtrght and Lloyd G. Alexander. (Final rept. for
period June 4, 1952 to June 30, 1954). viii, 108p.
diagrs., photos., 26 tabs. (Univ. of Okla. Research
The application of cyclonic flow to the combustion of
natural gas-air mixtures in emergent cyclonic free
jets, ducts, and diverging sections has been inves-
tigated. The investigation consists of quantitative
measurements to determine the characteristics and
stability limits of the flames obtained. In addition,
directional impact and static pressure tube measure-
ments were made in the flow fields of emergent
cyclonic free jets, so that the explanation to flame
stabilization due to cyclonic motion could be con-
RESEARCH ABSTRACTS NO. 81
Brown Univ., Providence, R.I. Div. of Applied
Mathematics. REMARKS ON TRANSFORMS AND
BOUNDARY VALUE PROBLEMS. P. Germain.
June 1954. 34p. (Brown Univ., Providence, R.I.
Div. of Applied Mathematics)
An attempt is made to show the relations between
transforms and simple boundary value problems.
Some general formulas show in fact that the Fourier
integral theorem, the Fourier Dini integral theorem
and many of the consequences which can be derived
from them may easily be generalized. The same
formulas can be applied as well to elliptic as to hy-
perbolic problems. It does not seem to be possible
to obtain correspondingly simple results for the case
of problems related to an equation of mixed type.
As an application of the approach, the interpretation
of a result, called a generalized Hankel Transform,
was made precise. The method and the results may
be extended to the case of finite transforms.
Brown Univ., Providence, R.I. Div. of Applied
Mathematics. AN EXPRESSION FOR THE GREEN'S
FUNCTION FOR A PARTICULAR TRICOMI PROB-
LEM. P. Germain. June 1954. 34p. diagrs.
(Brown Univ., Providence, R.I. Div. of Applied
The Tricomi equation is written with new indepen-
dent variables; this new form allows one to write
the Green's function for a special Tricomi problem
in the form of a Mellin Transform. The analysis is
greatly simplified by the use of a technique previously
used by R. Bader and the author. Corresponding
formulas for the doublet are given. These results
are given in a form which can be used for numerical
computation. Using the same method, a generalized
Tricomi problem is discussed. The results may be
used in order to simplify the existence proof for a
solution of a Triconi problem for the Tricomi
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