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Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Description: Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Date: March 9, 1951
Creator: Hubbartt, James E. & Schum, Eugene F.
Partner: UNT Libraries Government Documents Department

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

Flight determination of the drag and longitudinal stability and control characteristics of a rocket-powered model of a 60 degrees delta-wing airplane from Mach numbers 0.75 to 1.70

Description: Report discussing an investigation to determine the aerodynamic characteristics of a model of a tailless delta-wing airplane configuration with a leading edge swept back 60 degrees at a range of Mach numbers. Information about lift-curve slope, buffeting, drag rise, hinge-moment coefficients, transonic trim, and stability is provided.
Date: November 29, 1951
Creator: Mitcham, Grady L.; Crabill, Norman L. & Stevens, Joseph E.
Partner: UNT Libraries Government Documents Department

Flight performance of a twin-engine supersonic ram jet from 2,300 to 67,200 feet altitude

Description: Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.
Date: February 19, 1951
Creator: Dettwyler, H. Rudolph & Bond, Aleck C.
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

Flow separation ahead of a blunt axially symmetric body at Mach numbers 1.76 to 2.10

Description: The pressure distribution and drag were determined for a spherical-nosed axially symmetric body with thin projecting rods at Mach numbers of 1.76, 1.93, and 2.10. The upstream projection distance of the rods was varied over a wide range to study changes in the character of the flow separation and to determine the variation of drag and pressure distribution with tip projection. Drag coefficients between 0.18 and 0.30 were obtained for most tip projections at each Mach number.
Date: December 12, 1951
Creator: Moeckel, W E
Partner: UNT Libraries Government Documents Department

Free-jet tests of a 6.5-inch-diameter ram-jet engine at Mach numbers 1.81 and 2.00

Description: Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Date: March 7, 1951
Creator: Faget, Maxime A.; Watson, Raymond S. & Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Free-spinning tunnel investigation of a 1/20-scale model of the Douglas X-3 airplane

Description: Report discussing the spin and spin-recovery characteristics of a model of the Douglas X-3 airplane in a free-spinning tunnel. The pitching-moment characteristics of the scale model were not found to be typical of larger scale results. The results indicated that at an altitude range of 15,000 to 30,000 feet, the X-3 will not exhibit unusual trim tendencies and it will be difficult to obtain erect spins unless the ailerons are full with the spin.
Date: December 26, 1951
Creator: Hultz, Burton E.
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

An investigation of four wings of square plan form at a Mach number of 6.86 in the Langley 11-inch hypersonic tunnel

Description: Report presenting the results of pressure-distribution and force tests on four wings at Mach number 6.86 and Reynolds number 980,000 in the 11-inch hypersonic tunnel. Characteristics of the wings tested included a 4-inch square plan form, a 5-percent maximum thickness, and diamond, half-diamond, wedge, and half-circular-arc sections. Information about pressure measurements, wing characteristics, and Schlieren photographs is provided.
Date: June 29, 1951
Creator: McLellan, Charles H.; Bertram, Mitchel H. & Moore, John A.
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

An investigation of the aerodynamic characteristics of a series of cone-cylinder configurations at a Mach number of 6.86

Description: Report presenting the results of pressure-distribution and force tests of two cone-cylinder configurations and a comparison with theoretical calculations. The first series was made up of three configurations with 20 degree conical noses and cylindrical afterbodies with 0, 2, and 4 diameter lengths and the second was made up of cylindrical afterbodies with a diameter length and conical noses with apex angles of 10 to 180 degrees. Results regarding the pressure distributions, aerodynamic forces, and Schileren photographs are provided.
Date: December 17, 1951
Creator: Cooper, Ralph D. & Robinson, Raymond A.
Partner: UNT Libraries Government Documents Department

Investigation of the aerodynamic effects of an external store in combination with 60 degree delta and low-aspect-ratio tapered wings at a Mach number of 1.9

Description: Report presenting a wind-tunnel investigation of an external store of fineness ratio 8.6 on the chord plane of several low-aspect-ratio wings. Testing occurred at a Mach number of 1.9 on wings with 60 degree leading-edge sweepback and unswept trailing edges with taper ratios of 0 and 0.28 and on an unswept wing with a taper ratio of 0.625. Results regarding the loading breakdown, store position, and effect of store on control characteristics are provided.
Date: January 9, 1951
Creator: May, Ellery B., Jr.
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

Preliminary results of a determination of temperatures of flames by means of K-band microwave attenuation

Description: The temperature effects on the attenuation of K-band microwaves, at a frequency of 26,500 plus or minus 30 megacycles per second, through natural-gas and propane flames containing added alkali halide salts, were investigated over a temperature range from 1900 to 2500 K. The preliminary data of this investigation indicated that the attenuation varies appreciably with the sodium-line-reversal temperatures of the flames and is independent of the particular hydrocarbon fuels that were used for temperature sources and of the particular halide components of the compounds used in the concentrations employed to produce easily measurable attenuation. A reproducibility of plus or minus 25 K was obtainable.
Date: September 24, 1951
Creator: Rudlin, Leonard
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

Preliminary investigation of cooling-air ejector performance at pressure ratios from 1 to 10

Description: Preliminary investigation was made of conical cooling air ejector at primary pressure ratios from 1 to 10. The cooling-air flow was maintained at zero and the resulting pressure variation in the shroud indicated pumping ability. The cooling-air flow was maintained at zero and the resulting pressure variation in the shroud indicated pumping ability. The gross thrust of the ejector and nozzle were compared. Several ratios of the spacing between the nozzle and shroud exit to the nozzle exit diameter were investigated for several shroud to nozzle exit diameter ratios. Maximum gross thrust loss occurred under conditions of zero cooling-air flow and was as much as 35 percent below nozzle jet thrust. For minimum thrust loss, ejector should be designed with as low diameter and spacing ratio as possible.
Date: October 17, 1951
Creator: Ellis, C W; Hollister, D P & Sargent, A F , Jr
Partner: UNT Libraries Government Documents Department