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Exploratory investigation at high and low subsonic Mach numbers of two experimental 6-percent-thick airfoil sections designed to have high maximum lift coefficients

Description: Report presenting an investigation to determine if thin airfoils with increased values of low-speed maximum lift coefficient but also retain the basic advantages of thin sections at high Mach numbers can be developed. Several experimental thin airfoil sections were developed from an analysis of airfoil data and two of them were investigated at high and low subsonic Mach numbers. Results regarding the low-speed characteristics and high-speed characteristics are provided.
Date: December 14, 1951
Creator: Loftin, Laurence K., Jr. & von Doenhoff, Albert E.
Partner: UNT Libraries Government Documents Department

A flight study of requirements for satisfactory lateral oscillatory characteristics of fighter aircraft

Description: Report presenting a pilot-opinion survey conducted with a conventional fighter airplane fitted with special servo devices for varying in flight the dihedral effect, static directional stability, and directional damping. Results showing the boundaries that define satisfactory and tolerable lateral oscillatory characteristics are presented.
Date: July 25, 1951
Creator: Liddell, Charles J., Jr.; Creer, Brent Y. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Effects on control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degrees sweptback wing at a Mach number of 1.9

Description: Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.
Date: December 4, 1951
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics: transonic bump method

Description: Report presenting the results of an experimental investigation of the downwash and longitudinal stability characteristics of a semispan, triangular-wing airplane model with a horizontal tail. Lift, drag, and pitching-moment data re presented for the wing-fuselage combination. Results indicated that the model with the tail on or below the wing-chord plane possessed satisfactory stability characteristics throughout the test range of lift coefficient.
Date: August 17, 1951
Creator: Allen, Edwin C.
Partner: UNT Libraries Government Documents Department

Investigation of wing-tip ailerons on a 51.3 degrees sweptback wing at transonic speeds by the transonic-bump method

Description: Report presenting an investigation to determine the aerodynamic characteristics of deflectable wing-tip ailerons on a sweptback wing in the Langley high-speed tunnel by means of the transonic bump technique. Three ailerons were investigated, one with a basic wing-plan form and two with an extended-tip plan form. Results regarding the longitudinal aerodynamic characteristics, rolling-moment data, control effectiveness, and lift effectiveness are provided.
Date: November 26, 1951
Creator: Moseley, William C., Jr. & Watson, James M.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of a translating cowl technique for improving take-off performance of a sharp-lip supersonic diffuser

Description: A preliminary investigation was conducted in quiescent air on a translating cowl technique for improving the take-off performance of a sharp-lip supersonic diffuser. The technique consists of cutting the cowling in a plane normal to its axis and then translating the forepart of the cowling in the forward direction. The leading edge of the fixed portion of the cowling is rounded. Appreciable improved inlet performance was obtained with a cowling translation corresponding to a gap of only 1/4 inlet radius.
Date: November 28, 1951
Creator: Cortright, Edgar M., Jr.
Partner: UNT Libraries Government Documents Department

Method for estimating lift interference of wing-body combinations at supersonic speeds

Description: Report presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations to evaluate combinations with non-triangular wings. The method is applied to the prediction of lift-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.
Date: December 31, 1951
Creator: Nielsen, Jack N. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics

Description: Report presenting an investigation to determine the low-speed longitudinal characteristics of an aspect ratio 4 triangular wing alone and in combination with a fuselage, vertical tail, and horizontal tail. The complete model consisted of a wing with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail, and two thin, unswept, all-movable horizontal tails of two different aspect ratios.
Date: October 16, 1951
Creator: Graham, David & Koenig, David G.
Partner: UNT Libraries Government Documents Department

A summary of available knowledge concerning skin friction and heat transfer and its application to the design of high-speed missiles

Description: Review of certain characteristics necessary to determine skin friction and heat transfer on the surfaces of high-speed missiles, including temperature recovery, skin-friction coefficients and heat-transfer coefficients of laminar and turbulent boundary layers, and the position of the transition from laminar to turbulent flow. A comparison is also made between existing flight data and results computed by the boundary-layer momentum-integral method in an attempt to establish design criteria for missiles that are very different from the typical shape.
Date: November 9, 1951
Creator: Rubesin, Morris W.; Rumsey, Charles B. & Varga, Steven A.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a 1/4-scale Bell X-5 airplane model

Description: From Summary: "This paper contains the results of measurements at 20 degrees and 60 degrees wing sweep of the low-speed pressure distribution on the wing, wing slat, wing leading-edge fillet, and fuselage of a 1/4-scale model of a preliminary Bell X-5 airplane design. The pressure-distribution measurements were made to obtain specific aerodynamic load information for application to the Bell X-5 airplane. Some of the results, however, are useful for application to swept-wing airplanes in general."
Date: December 4, 1951
Creator: Kemp, William B., Jr. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Flame velocities over a wide composition range for pentane-air, ethylene-air, and propyne-air flames

Description: Fundamental flame velocities are reported for pentane air, ethylene-air, and propylene-air mixtures for the concentration range 60 to 130 percent of stoichiometric. A form of the Tanford and Pease equation, which includes a small constant velocity term independent of diffusion, will predict the observed changes in flame velocity.
Date: October 18, 1951
Creator: Simon, Dorothy M. & Wong, Edgar L.
Partner: UNT Libraries Government Documents Department

Full-scale investigation of cooling shroud and ejector nozzle for a turbojet engine: afterburner installation

Description: From Summary: "A full-scale ejector cooling investigation was made on a turbojet engine - afterburner installation in the NACA Lewis altitude wind tunnel. Ejector performance was studied at primary exhaust-gas temperatures from 2700 degrees to 3400 degrees R (corresponding to ejector temperature ratios from 2.0 to 5.0), primary pressure ratios from 1.79 to 3.4, secondary air flows up to 29 percent of the primary gas flow, and for diameter ratios from 1.08 to 1.42 and spacing ratios from 0.04 to 1.16. In addition, variations were made in the primary exhaust-nozzle area."
Date: December 17, 1951
Creator: Wallner, Lewis E. & Jansen, Emmert T.
Partner: UNT Libraries Government Documents Department

Free-spinning tunnel investigation of the 1/21-scale model of the Chance Vought F7U-3 airplane: TED No. NACA DE 362

Description: Report presenting an investigation of a 1/21-scale model of the Chance Vought F7U-3 airplane in the 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics for combat loading in the clean condition. Results regarding erect spins, inverted spins, spin-recovery parachutes, and recommended recovery technique are provided.
Date: November 9, 1951
Creator: Klinar, Walter J. & Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Dynamic stability and control characteristics of a delta-wing vertically rising airplane model in take-offs, landings, and hovering flight

Description: Report presenting an investigation by means of tests of a flying model in still air to determine the dynamic stability and control characteristics of a delta-wing vertically rising airplane in take-off, landing, and hovering phases of flight. The uncontrolled pitching motion consisted of an unstable oscillation which was more unstable with a rearward than with the normal center-of-gravity location.
Date: October 9, 1951
Creator: Lovell, Powell M.; Bates, William R. & Smith, Charles C., Jr.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

Description: Report presenting an investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller was conducted int he 16-foot high-speed tunnel over a range of blade-angle settings. Two related straight propellers were also tested over the same operating range as the swept propeller. Results regarding envelope efficiency, effect of compressibility on maximum efficiency, effect of sweep on power coefficient, constant-power propeller operation, and effect of sweep on propeller-blade loading are provided.
Date: January 4, 1951
Creator: Evans, Albert J. & Liner, George
Partner: UNT Libraries Government Documents Department

Preliminary evaluation of the air and fuel specific-impulse characteristics of several potential ram-jet fuels 4: hydrogen, a-methylnaphthalene, and carbon

Description: A preliminary analytical evaluation of the air and fuel specific-impulse characteristics of hydrogen, a-methylnapthalene, and graphite carbon has been made. Adiabatic constant-pressure combustion flame temperatures for each fuel at several equivalence ratios were calculated for an initial air temperature of 560 degrees R and a pressure of 2 atmospheres.
Date: August 31, 1951
Creator: Gammon, Benson E.
Partner: UNT Libraries Government Documents Department

Data presentation of force characteristics of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Investigation to determine lift, drag, and pitching-moment characteristics of several engine-strut-body combinations was conducted over range of angles of attack from 0 degrees to 10 degrees at Mach numbers of 1.8 and 2.0. The average Reynolds number based on body length was 28x106. Data are presented without analysis and indicate decreases in minimum drag and lift curve slope with decreasing in minimum drag and lift curve slope with decreasing strut length. Decreases in minimum drag also noted with rear-ward movement of engines.
Date: August 14, 1951
Creator: Madden, Robert T. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department

Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine

Description: Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.
Date: March 5, 1951
Creator: Cook, William P. & Butze, Helmut F.
Partner: UNT Libraries Government Documents Department

Liquid-fuel-distribution and fuel-state effects on combustion performance of a single tubular combustor

Description: Report presenting an investigation to study the effects of liquid-fuel distribution on combustion performance of a single turbojet-engine combustor operating with liquid MIL-F 5624 fuel. Results regarding altitude limits and combustion efficiencies, liquid-fuel distribution, fuel state, and miscellaneous observations are provided.
Date: May 1, 1951
Creator: McCafferty, Richard J.
Partner: UNT Libraries Government Documents Department

A specially constructed metallograph for use at elevated temperatures

Description: "A metallographic microscope was developed with provision for heating a specimen to 1800 F in protective atmospheres, that is, vacuum or gas. A special objective was constructed of reflecting elements with an unusually long working distance (7/16 in.) and a high numerical aperture (0.5). Changes in specimen microstructure were observed and recorded on 35-millimeter motion-picture film. The resulting pictures were projected as motion pictures and individual frames were cut and enlargements made for close observation" (p. 1).
Date: September 11, 1951
Creator: Jenkins, Joe E.; Buchele, Donald R. & Long, Roger A.
Partner: UNT Libraries Government Documents Department

A simplified instrument for recording and indicating frequency and intensity of icing conditions encountered in flight

Description: "An instrument for recording and indicating the frequency and intensity of aircraft icing conditions encountered in flight has been developed by the NACA Lewis Laboratory to obtain statistical icing data over world-wide air routes during routine airline operations. The operation of the instrument is based on the creation of a differential pressure between an ice-free total-pressure system and a total-pressure system in which small total-pressure holes vented to static pressure are allowed to plug with ice accretion. The simplicity of this operating principle permits automatic operation, and provides relative freedom from maintenance and operating problems" (p. 1).
Date: July 3, 1951
Creator: Perkins, Porter J.; McCullough, Stuart & Lewis, Ralph D.
Partner: UNT Libraries Government Documents Department

Schlieren investigation of the wing shock-wave boundary-layer interaction in flight

Description: Report presenting data obtained in flight using a schileren apparatus that photographed the shock-wave interaction with a thick turbulent boundary layer on a wing. Local Mach number and boundary-layer characteristics obtained from pressure measurements in the vicinity of the shock wave are also presented.
Date: September 19, 1951
Creator: Cooper, George E. & Bray, Richard S.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

Description: "An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones" (p. 1).
Date: November 5, 1951
Creator: Jack, John R.
Partner: UNT Libraries Government Documents Department