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Natioan Advisory Committee For Aeronautics ,7Research Abstracts NO. 81 t. 5 APRIL 20, 19 55 .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, p. 8744). 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. 18571866) 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 N155 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 N155 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 loadcarrying ability of heatresistant 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. erany dissociating element for which the necessary data exist. ReSults jre given for hydrogen, oxygen, and pilogen.",The efect of dissociation on the heat c.... cpa .jV !did briefly. NA'N 3282 R NULAR CORROSION OF HIGHPURITY '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 singlephase highpurity aluminum in 20 percent hydrochloric acid as a function of iron content and finalannealing temperature is attributed to the segregation to atomic sites in the grainboundary 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 these sites. 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 TN 3326) 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 skinfriction and heattransfer results. Knowledge of velocity or temperature profiles is not necessary in using this calculation method. When the method is applied to a convergentdivergent, axially sym metric rocket nozzle, it shows that high rates of *AVAILABLE ON LOAN ONLY. .ADDRESS REQUESTS FOR DOCUMENTS TO NACA, 1512 H ST., NW., WASHINGTON 25, D. C., CITING CODE NUMBER ABOVE EACH TITLE, iHE REPORT TITLE AND AUTHOR. ,, .1, 30 c. L", rSv 2 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 constantstress creep tests, constantloadrate tests, and constantload 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 highresolution Xray 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 liftingsurface 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 aileronreversal speed are computed by the use of a Galerkintype 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 thinairfoil 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 halfdelta 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. Endplate effects for several of the derivatives are also considered. NACA RESEARCH ABSTRACTS NO. 81 NACA TN 3376 THE EFFECT OF CONTROL STIFFNESS AND FOR WARD SPEED ON THE FLUTTER OF A 1/10SCALE DYNAMIC MODEL OF A TWOBLADE JETDRIVEN 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 1/10scale dynam ic model of a twoblade jetdrive helicopter to study the effects of bladepitchcontrol 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 bladepitchcontrol 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 tipspeed 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 lowspeed, lowturbulence 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 boundarylayer 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 fightertype aircraft. One is an electromechanical selfbalancing 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 freestream 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 10caliber tangent ogive with a cylind rical alterbody. The variation of base pressure co efficient with freestream Mach number and NACA RESEARCH ABSTRACTS NO. 81 Reynolds number was determined for laminar, transitional, and turbulentboundarylayer flow. Some effects of body fineness ratio, noseprofile shape, and afterbody shape (boattail) were also in cluded in the investigation. NACA TN 3420 HYDRODYNAMIC TARES AND INTERFERENCE EFFECTS FOR A 12PERCENTTHICK SURFACE PIERCING STRUT AND AN ASPECTRATIO0.25 LIFTING SURFACE. John A. Ramsen and Victor L. Vaughan, Jr. April 1955. 20p. diagrs. (NACA TN 3420) Results are presented from an investigation of the hydrodynamic tares and interference acting on an NACA 661012 airfoilsection surfacepiercing strut and.an aspectratio0.25 modifiedflatplate 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. Struttare effects were appreciable only on drag, where sectiondrag coef ficients showed good agreement with data from pre vious tank and windtunnel tests. The surface intersection drag coefficients were constant above the critical wave speed and showed fairly good agreement with wavedrag theory below the critical speed. NACA TN 3426 AN EXPERIMENTAL STUDY OF ORIFICE COEF FICIENTS, INTERNAL STRUT PRESSURES, AND LOADS ON A SMALL OLEOPNEUMATIC SHOCK STRUT. James H. Walls. April 1955. 23p. diagrs., photos. (NACA TN 3426) Measurements of shockstrut internal pressures, telescoping velocity, and strut stroke were made during drop tests of a small oleopneumatic 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 internalpressure 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 GROUNDSIMULATOR 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 controlstick 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. 3 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 LEADINGEDGE SEPARATION. Clinton E. Brown and William H. Michael, Jr. April 1955. 27p. diagrs. (NACA TN 3430) The slenderbody 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 forcefree 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 sheetstringer 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 PROPELLERSLIPSTREAM TOTALPRESSURE 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 twinengine 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 propellerthrust indicator, which samples the totalpressure 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. 4 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 pilottraining 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 ISOOCTANEAIR 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, NH3air 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 NH3air 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 TN 3447) 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 BEEPCONTROL SYSTEM. Howard L. Turner, John S. White and Rudolph D. Van Dyke, Jr. March 1955. 55p. diagrs., photos., tab. (NACA TN 3496. Formerly RM A52A29) A comparison between manual control and remote control showed that a beeptype, radioremote control system was, in general, a satisfactory means of control for conducting standard handing quality flight tests. The dynamic characteristics of the airplaneautopilot combination and the selection of the proper parameter adjustments are discussed. NACA RESEARCH ABSTRACTS NO. 81 BRITISH REPORTS N36289" 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 stress distribution. N36290( 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 threedimensional 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 liftincidence 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 tunnel. N36381' 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 coneflat 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 coneflat plate relation is within 6 percent of an empirical relation analogous to the F laminar boundary layer factor. NACA RESEARCH ABSTRACTS NO.81 N36382' 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 200300 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. N36383* 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 EL. 1485) Measurements have been made of the voltage and current in dc 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. N36385* 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. N36386' 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) 5 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 4 percent. UNPUBLISHED PAPERS N35767 * 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. 112119) 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. N35826' Univ. of Calif., Berkeley. Institute of Engineering Research. A MACH 3.106 TWODIMENSIONAL 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. HE150120) 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 boundarylayer 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 ary layer. N35827* 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. PIBAL 225) 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. N35828' 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 only. N35829' 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 Institute) The application of cyclonic flow to the combustion of natural gasair 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 clusively established. NACA RESEARCH ABSTRACTS NO. 81 N35830' 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. N35831' 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 Mathematics) 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 equation. NACALangley 42055 4M NACA REQUEST FORM Date____________ 19___ Name Organization Street address NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 1512 H Street, N.W. Washington 25, D. C. Division of Research Information The Committee is pleased to forward the enclosed pub lications in accordance with your recent request. We regret that the remaining items are not enclosed for the reasons) indicated. A._Out of print. B._Will supply when released. C._Not an NACA document. Request from D. Available on loan only. E.Photocopies available at Photoduplicatidn Service, Library of Congress. F._Cannot identify docu _ment requested. G. _Classified document. Request through mili tary project officer. H.Withdrawn from cir culation. I._Not available for cir culation. Documents on loan to be returned by Gity, Zone No., and State Item Quantity Code Title and Author NACA No. desired number (Only Needed When Code Number Unavailable) Action 1 2 3 4 5 6 7 8 9 Signature POLICY OF NACA ON DISTRIBUTION OF THEIR PUBLICATIONS NACA Reports, Technical Notes, and Technical Memorandums are available for a period of 5 years, after that, most of them can be had only on a loan basis. All Wartime Reports are in this category. All loan material should be returned promptly at the expiration of the loan period to the following address: Langley Aeronautical Laboratory, Langley Field, Virginia ATTENTION: Mr. Walter H. Lee. British publications currently listed on the Research Abstracts are available only on loan. However, should a British paper be of particular interest and if you will so advise this office, your name will be placed on our waiting list to receive a copy if and when retention copies can be furnished. Please fill in the requested information below since the above part of this form will be returned with the documents requested. I Date 19 lame organization street address ty. Zone No.. and State a.9.. Do Not Write in This Space UNtVERSI' OF FLORIDA 3162aa os153 24433 3 
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