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NACA RM 54D19 PRELIMINARY MEASUREMENTS OF TURBULENCE AND TEMPERATURE FLUCTUATIONS BEHIND A HEATED GRID. A. L. Kistler, V. O'Brien and S. Corrsin, Johns Hopkins University. June 1954. 24p. diagrs., photo. (NACA RM 54D)19) Preliminary measurements have been made of velocity and temperature fluctuations in the flow be hind a heated grid in a uniform air stream. Tem perature correlation shows a reasonable degree of isotropy, and the temperature fluctuations die out at large distances more slowly than the turbulence, as has been predicted theoretically under some strongly simplifying postulates. NACA TN 3072 A THEORETICAL INVESTIGATION OF THE AERO DYNAMICS OF WINGTAIL COMBINATIONS PER FORMING TIMEDEPENDENT MOTIONS AT SUPERSONIC SPEEDS. John C. Martin, Margaret S. Diederich and Percy J. Bobbtitt. May 1954. 226p. ~~diagra tab. (NACA TN 3072) A 11s.reticrlal Investigation is presented on the con i rfllestIr.n ...fth horizontal tail to the lift and plrconup~ nlmort" due ~to gle of attack, a constant rate of ..):tch, and a conlstant vertical acceleration. Numer (al vallues ... the aerodynamic coefficients associated wlth these n...ts...ns are presented for a number of /(w:,r'dlnlensl..nalI wingtail combinations, a triangular muu;triangulalrtail combination, and a number of ftcalanular wingtriangulartail combinations. A .method of treating unsteady aerodynamics based on an infinite series of stabasel .ier staat srIr of successively higher order is presented. Methods for calculat ing the flow fields behind winlgs with a constant vertical acceleration are developed. Calculated re sults are presented for the upwash behind two dimensional wings and for certain regions behind triangular and rectangular wings for a constant rate of pitch and for a constant rate of vertical accelera tion. NACA TN 3150 METHOD FOR RAPID DETERMINATION OF PRES SURE CHANGE FOR ONEDIMENSIONAL FLOW WITH HEAT TRANSFER, FRICTION, ROTATION, AND AREA CHANGE. James E. Hubbartt, Henry O. Slone and Vernon L. Arne. June 1954, 22p. diagrs., 2 tabs. (NACA TN 3150) An approximate method for rapid determination of the pressure change for subsonic flow of a com pressible fluid under the simultaneous action of heat transfer, friction, rotation, and area change is de veloped. In the development of this method, the momentum equation was approximated and re CURRENT NACA REPORTS NACA Rept. 1132 LAMIINAR BOUNDARY LAYER ON CONE IN SUPER SONIC FLOW AT LARGE ANGLE OF ATTACK. Franklin K. Moore. Appendix B: NUMERICAL SOLUTION OF DIFFERENTIAL EQUATIONS. Lynn Albers. 1953. ii,13p. diagrs. (NACA Rept. 1132. Formerly TN 2844) The laminar boundarylayer flow about a cone at large angles of attack to a supersonic stream has been analyzed in the plane of symmetry. At the bottom of the cone, velocity profiles were obtained showing the expected tendency of the boundary layer to become thinner on the under side of the cone as the angle of attack is increased. At the top of the cone, the analysis failed to yield unique solutions, except for small angle of attack. Beyond a certain critical angle of attack, boundarylayer flow does not exist in the plane of symmetry, thus indicating separation. ' NACA Rept. 1139 . CHARTS AND APPROXIMATE FORMULAS i~HE ESTIMATION OF AEROELASTIC EFFECT I jTHE LATERAL CONTROL OF SWEPT AND UN UE'q!}[ I WINGS. Kenneth A. Foss and Franklin H'. Diederich. 1953. iii, 25p. diagrs.. 2jtabs (NACA Rept. 1139. Formerly TN 2747) Charts and approximate formulas are presented Mr +4 the estimation of static aeroelastic effects on the  spanwise lift distribution, rollingmoment coeffi cient, and rate of roll due to aileron deflections on swept and unswept wings at subsonic and supersonic speeds. Some design considerations brought out by the results of this paper are discussed. NACA Rept. 1148 A SPECIAL INVESTIGATION TO DEVELOP A GENERAL METHOD FOR THREEDIMENSIONAL PHOTOELASTIC STRESS ANALYSIS. M. M. Frocht and R. Guernsey, Jr., Illinois Institute of Technology* 1953. ii, 17p. diagrs., photos., 3 tabs. (NACA Rept. 1148. Formerly TN 2822) The method of strain measurement after annealing is reviewed and found to be unsatisfactory for the materials available in this country. A new, general method is described for the photoelastic determina tion of the principal stresses at any point of a gen eral body subjected to arbitrary loads. The method has been applied to a sphere subjected to diameltral compressive loads. The results show possibilities of high accuracy. *AVAILABLE ON LOAN ONLY. ADDRESS REQUESTS FOR DOCUMENTS TO NACA, 1512n H ST., NW., THE REPORT TITLE AND AUTHOR. WASHINGTON Is. D. C., CITING CODE NUMBER ABOVE EACH TITLE; National Advisory Committee For Ae~ronautics Research Abstracts libE_ 22 .1.~954 NO. 65 arranged for a convenient solution employing charts. This report presents the analysis involved in simpli fying the momentum equation, the charts necessary for obtaining particular solutions, and comparisons with more rigorous numerical solutions with condi tions typical for aircooled turbine blades. NACA TN 3174 INFLUENCE OF AIRFOIL TRAILINGEDGE ANGLE AND TRAILINGEDGETHICKNESS VARIATION ON THE EFFECTIVENESS OF A PLAIN FLAP AT HIGH SUBSONIC MACH NUMBERS. Albert D. Hemenover and Donald J. Graham. June 1954. 101p. diagrs., photos., 5 tabs. (NACA TN 3174. Formerly RM A51C12a) The effects of variation of trailingedge angle and trailingedge thickness on the characteristics of a 10percentchord thick NACA airfoil section with a 25percentchord plain flap are appraised from windtunnel tests at Mach numbers from 0.3 to 0.9 and Reynolds numbers varying correspondingly from 1 to 2 million. The airfoil trailingedge angle was varied from 180 to 60, and the trailingedge thick ness from zero to the thickness at the flap hinge line. NACA TN 3207 ROLE OF NICKEL DIP IN ENAMELING OF SHEET STEEL. D. G. Moore, J. W. Pitts and W. N' Harrison, National Bureau of Standards. June 1954. 27p. diagrs., photos., 8 tabs. (NACA TN 3207) An investigation was made of the effects of the firing time and the weight of the nickel deposited from the nickeldip solution on the adherence developed by a cobaltfree and a cobaltbearing groundcoat enamel on both enameling iron and a titaniumbearing low carbon steel. NACA TN 3215 TESTS OF BONDED AND RIVETED SHEET STRINGER PANELS. Leonard Mordfin and I. E. Wilks, National Bureau of Standards. June 1954. 45p. diagrs., photos., 5 tabs. (NACA TN 3215) Bending and compression tests were performed on 21 sheetstringer panels of 75ST6 aluminum alloy having alclad sheets nominally 0.051 inch thick and stringers nominally 31/2 inches apart. Nine panels had Istringers bonded to the sheets with Araldite Type I adhesive, three panels had Istringers bonded to the sheets with Metlbond adhesive, and nine panels had Zstringers riveted to the sheets. All tests were carried to failure and strain and deformation measurements were made. The test results did not indicate any great superiority of one type of con struction over the other but rather that the choice in any given case would depend upon the particular de signs being compared. They also showed that the riee co="stu t ;n and h hd cla ag a n always the governing factor in the strength of bonded panels. NACA RESEARCH ABSTRACTS NO. 65 BIRITISH REPORTS N30793* Royal Aircraft Establishment (Gt. Brit.) A HIGH SPEED ELECTROMECHANICAL MULTI PLIER. C. A. A. Wass and D. W. Allen. February 1954. 13p. diagrs., photos. (RAE Tech.Note GW 300) Requirements exist in simulator work for a simple highspeed squaring and multiplying unit of moderate accuracy. This note describes a simple electro mechanical multiplier using a type E.4 relay as a position servo driving a potentiometer. The unit will operate on frequencies up to 15 eps without intro ducing any appreciable phase shift. Accuracy de pends primarily on the quality of the potentiometers used but maximum errors of 1 percent of the maxi mum output appear possible. N30835* Royal Aircraft Establishment (Gt. Brit.) A NOTE ON THE USE OF STRAIN GAUGES IN WIND TUNNEL BALANCES. J. R. Anderson. January 1954. 28p. diagrs., photos. (RAE Tech.Note Aero 2290) This note is substantially that presented at the NATO/AGARD wind tunnel and model testing panel on September 3, 1953. It reviews briefly some of the experience obtained in the employment of wind tunnel balances using bonded, resistance type elec trical strain gages, in the smaller highspeed wind tunnels of Aerodynamics Department. The effects of temperature on the strain gages are discussed and shown to be a major limitation in their use. A self  balancing potentiometer instrument, specially de signed and developed for use with windtunnel strain gage balances, is also described briefly. N30837t Marine Aircraft Experimental Establishment (Gt. Brit. ) THE DEVELOPMENT OF A MINIATURE PRESSURE PICKUP. J. K. Friswell. March 1954. 10p. diagrs., photos. (MAEE F/TN/3) Details are given of the construction of a miniature pressure pickup of the diaphragm and straingaged cantilever type. The unit is cylindrical, with over all diameter 1 inch and overall length 2 inches, its weight being 1. 9 ounces. It is designed to operate in te range 020 esiand bilrcodee r po tie easy to service. NACA RESEARCH ABSTRACTS NO. 65 N30839 Marine Aircraft Experimental Establishment (Gt. Brit. ) ASSESSMENT OF REVERSIBLE PITCH PROPELLER TRAIL INSTALLATION SOLENT N. J.201. J. Taylor. March 1954. 23p. diagrs., photos., 2 tabs. (MAEE F. TX '2) An assessment was required on the operation of the reversible pitch propeller trial installation, on the Solent N. J. 201, as part of a general research pro gram for seaplanes. Results are given with the reversing pitch propellers fitted to the inboard engines in tests on low speed maneuvering, partic ularly in buoy approaches, and when used as braking units during landing. Some brief turning circle measurements have also been done. N30843* Aeronautical Research Council (Gt. Brit. ) THE PERFORMANCE OF THE 108 COMPRESSOR FITTED WITH LOW STAGGER FREE VORTEX BLADING. D. V. Foster. 1954, 36p. diagrs., photos. (ARC CP 144) A large threestage compressor is described which is designed for detail threedimensional flow inves tigations. Particular attention has been paid to the accuracy of measurement on the rig and it is shown that, the main errors are due to the unsteady nature of the flow and to speed fluctuations. Test charac teristics of the first set of low stagger free vortex blading are presented and compared with various theoretical performance calculations. A description of the surging behavior of the compressor and the effect of blade position upon the measured static pressure are given. N30844+ Aeronautical Research Council (Gt. Brit. ) ZERO LIFT DRAG MEASUREMENTS ON SWEPT WINGS AT TRANSONIC AN SUPERSONIC SPEEDS USING THE GROUNDLAUNCHED ROCKET BOOSTED MODEL TECHNIQUE. T. Lawrence and C. Kell. 1954. 35p. diagrs., photo., tab. (ARC CP 145) This is mainly a documentary record of drag meas urements on 14 swept wings varying in plan form from deltas to swept untapered wings from 4 percent to 10 percent thick. Results are compared with theory for wrings of doublewedge section; an attempt is made to check the validity of supersonic similarity laws. Three primary conclusions are drawn; at supersonic speeds, wave drag of a given wing varies as the square of thickness ratio; supersonic similar ity law allows drag of "similar" wings to be com pared; drag of roundnose wings perhaps may be estimated from calculations of drag of doublewedge wings. N30845" Aeronautical Research Counlcil (Gt. Brit. ) VIBRATION AND FLUTTER OF AIRCRAFT AERIALS. W. H. Johnson. 1954. 15p. diagrs., photos. (ARC CP 14tI? To swl failures of blade and whip aircraft aerials have been investigated and it is shown that stalling flutter and mechanically excited vibration hav~e both contributed in large measure to the failures. All the aerial types involved possess considerable 111 .t. Inl, and very low internal damping. It is shown that the introduction of damping into the neunting, of the aerials has a very beneficial effect on their behavior as regards both flutter and mechanically excited vibration. Methods are described for preventing failure from either cause. N30846' Aeronautical Research Council (Gt. Brit. ) FACTORS INFLUENCING THE OPTIMUM AERO DYNAMIC DESIGN OF COOLED TURBINES. G. F. C. Rogers. 1954. 27p. diagrs. (ARC CP 155) Owing to the losses in performance which increase with the rate of heat extraction required for turbine cooling, it is desirable to know what range of aero dynamic designs is associated with low values of this quantity. Different aerodynamic designs of turbine, all passing the same mass flow and having approxi niately the same disc and blade stresses, have been compared on the basis of the ratio of heat extraction rate to work output. It is found that high values of flow coefficient are beneficial in this respect, and that impulse turbines have a slight advantage over reaction turbines. N30847* Aeronautical Research Council (Gt. Brit.) THE EFFECT OF ROLLING ON FINAND)RUDDER LOADS IN YAWING MANOEUVRES. D. R. Puttock. 1954. 31p. diagrs., 3tabs. (ARC CP 153) Exact solutions are derived for angle of sidestip and finandrudder loads for an aircraft performing two yawing maneuvers induced by the rudder. Angles of sideslip and finandrudder loads are then calculated for three selected aircraft and compared with results obtained by a simplified method in which rolling motion is neglected. Further calculations are made using a modified method in which the coefficients of the response formulas of the simplified method have been adjusted to take some account of rolling. The analysis shows that errors of 20 percent may be incurred if rolling is neglected in the estimation of finandrudder loads for aircraft with swept and delta wings. R ARCH ABSTRACTS NO. 65 N30895' Royal Aircraft Establishmlent (Gt. Brit.) SECONDARY FLOW IN A BOUNDARY LAYER. L. Sowerby. March 1954. 21p. diagrs., tab. (RAE Aero 2512) The laminar boundary layer on a flat plate is con sidered. It is shown that a secondary flow in the boundary layer is a consequence of curvature in the streamlines of the mainstream flow (in planes paral lel to the plate). The special case in which the streamlines form a family of translates is discussed and the equations of possible families of streamlines are determined. The boundarylayer equations are solved in the case where the streamlines are a family of equal parabolas; this leads to an extension of Blasius' result for uniform flow over a flat plate. Finally, in the appendix, the skin friction coefficient is calculated, from which is obtained a quantity anal_ ogous to the profiledrag coefficient of a swept wing, for comparison with the results of Weber and Brebner for the latter case. The comparison confirms the assumptions made by them in the development of their theory. N30898* Royal Aircraft Establishment (Gt. Brit.) NOTES ON THE RESPONSE OF A LINEAR VIBRA TION SYSTEM TO IMPACT LOADING. H. K. P. Neubert. March 1954. 21p. diagrs. (RAE Tech. Note Instn. 138) In the course of investigations into the effect of im pact loadings, the general equations for deflection, velocity, and acceleration of a linear system of one degree of freedom with velocity damping have been derived for a case of a mass being dropped onto a spring (with negligible mass). Response curves are plotted and discussed for two idealized cases of air craft landing, and for a drop table test. TIhe possible errors for a proposed integrating touchdown velocity meter are discussed. FIrequene,: spectra for three typical impact curves have been computed and the error introduced when measuring the impact with an accelerometer of inadequate frequency response is discussed. MIISCELLANEOUS NACA Rept. 1028 Errata No. 1 on "EFFECT OF ASPECT RATIO ON THE AIR FORCES AND MOMENTS OF HARMON ICALLY OSCILLATING THIN RECTANGULAR WINGS INJ SUPERSONIC POTENTIAL FLOW." Charles E. Watkins. 1951. NACALangley 62254 4M illUNIVERSliTY OF FLORIDA1 31262 08153 117 9 UNPUBLISHED PAPERS N1726f ON SEVERAL MEASURES, TAKEN IN PRACTICE, FOR ELIMINATING OSCILLATORY YAW WITH FREE RUDDER. (Ujber einige praktisch durchgeffihrte Massnahmen zur Beseitigung von Gierschwingungen mit losem Ruder). R. Schmidt. April 1954. 10p. diagrs., photo. (Trans. from Lilienthal Gesellschaft fur Luftfahrtforschung, Berlin, Bericht 143, Nov. 67, 1941, p. 2224) Measures, tested and carried out on several air planes at Dornier works when unsatisfactorily damped oscillatory yaw had occurred, and its elimi inationn by modifications of the tail had not been pos sible, are discussed. The two groups of measures discussed are measures which augment the increase of rudder moment in the region of zero position of the controls; and measures which impede the free motion relative to the air of the rudder. N31386* MEASURES FOR ELIMINATION OF OSCILLATORY YAW WITH FREE RUDDER. (Massnahmen zur Beseitigung von Gierschwingungen mit losem Seitenruder). H. G. Schumann. April 1954. 6p. diagrs. (Trans. from LilienthalGesellschaft fur Luftfahrtforschung, Berlin, Bericht 143, Nov. 67, 1941, p. 2729) Experiences are given which were made with the Ju 88 in controlling oscillatory yaw with free rudder. This method of attaining the degree of rudder load reduction required in the individual case by the con trol force itself, involved the return to harmless variations of rudderselfadjustment and eliminated thus for a long time the difficulties occurring now and again at other firms. N31449t THEORETICAL AND EXPERIMENTAL STUDY OF THE MEANS OF PROTECTING AN AIRPLANE FROM GUST ACCELERATIONS. CHAPTER VIII  EXPERIMENITAL STUDY. (Recherches the~oriques et expkrimentales sur les moyens de soustraire un avion aux accelbrations que peuvent engendrer les perturbations atmosphiriques. Chapitre VIII  Etude expi~rimentale). Rene Hirsch. February 1954. 45fp. diagrs., photos. (Trans. from Ministere de l'Air. Publications Scientifiques et Techniques, no. 138, 1938) Changes in direction and intensity of the relative wind which strikes the airplane in flight induce changes in the total, hinge moment of the controlled aileron so that the consecutive rotations of the latter produce exactly defined variations of the total lift coefficient. Two basic airfoils were studied, the Potes 403 and NACA 23012. 
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