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Flight and preflight tests of a ram jet burning magnesium slurry fuel and utilizing a solid-propellant gas generator for fuel expulsion

Description: Data obtained from the first flight test of a ram jet utilizing a magnesium slurry fuel are presented. The ram jet accelerated from a Mach number of 1.75 to a Mach number of 3.48 in 15.5 seconds. During this period a maximum values of air specific impulse and gross thrust coefficient were calculated to be 151 seconds and 0.658, respectively. The rocket gas generator used as a fuel-pumping system operated successfully.
Date: April 6, 1955
Creator: Bartlett, Walter A., Jr. & Hagginbothom, William K., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of a high-flow transonic-compressor inlet stage having a hub-tip radius of 0.35

Description: Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.
Date: March 6, 1958
Creator: Felix, A. Richard
Partner: UNT Libraries Government Documents Department

Initial experiments on flutter of unswept cantilever wings at Mach number 1.3

Description: Report presenting the results of a preliminary experimental flutter investigation of widely different unswept cantilever wings at Mach number 1.3. Wings with a variety of mass-density parameters, center-of-gravity positions, and elastic-axis positions were tested.
Date: January 6, 1949
Creator: Tuovila, W. J.; Baker, John E. & Regier, Arthur A.
Partner: UNT Libraries Government Documents Department

Investigation of pressure recovery of a single-conical-shock nose inlet at Mach number 5.4

Description: An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.
Date: April 6, 1953
Creator: Bernstein, Harry & Haefeli, Rudolph C
Partner: UNT Libraries Government Documents Department

Performance of single-stage compressor designed on basis of constant total enthalpy with symmetrical velocity diagram at all radii and velocity ratio of 0.7 at rotor hub / Jack R. Burtt and Robert J. Jackson

Description: A typical inlet axial-flow compressor inlet stage, which was designed on the basis of constant total enthalpy with symmetrical velocity diagram at all radii, was investigated. At a tip speed of 1126 feet per second, a peak pressure ratio of 1.28 was obtained at an efficiency of 0.76. At a tip speed, the highest practical flow was 28 pounds per second per square foot frontal area with an efficiency of 0.78. Data for a rotor relative inlet Mach number range of from 0.5 to 0.875 indicates that the critical value for any stage radial element is approximately 0.80 for the stage investigated.
Date: September 6, 1951
Creator: Burtt, Jack R & Jackson, Robert J
Partner: UNT Libraries Government Documents Department

Preliminary results of natural icing of an axial-flow turbojet engine

Description: Report presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Results regarding the tail-pipe temperature, engine jet thrust, and characteristics of ice formation are provided. No general conclusions can be reached from the data because the icing condition was relatively light.
Date: August 6, 1948
Creator: Acker, Loren W.
Partner: UNT Libraries Government Documents Department

Preliminary tank tests of some hydro-ski-wheel combinations in the planing condition

Description: Report presenting an investigation of the planing characteristics of various combinations of a wheel and a hydro-ski. Models tested included at least two values of the following parameters: diameter of wheel, width of wheel, cross-section shape of wheel, fore-and-aft location of wheel, lateral location of wheel, gap between wheel and ski, rotation of wheel, and protrusion of wheel. Results regarding the general effect of a wheel, effect of wheel shape and size, effect of wheel-ski arrangement, and possible methods of reducing resistance are provided.
Date: October 6, 1952
Creator: Land, Norman S. & Fontana, Rudolph E.
Partner: UNT Libraries Government Documents Department

Pressure and force characteristics at transonic speeds of a submerged divergent-walled air inlet on a body of revolution

Description: Report presenting an investigation in the transonic tunnel on a submerged inlet with a divergent-walled approach ramp to determine flow phenomena, pressure recovery, and external forces to provide correlation with available data obtained on similar inlets. Results regarding the pressure characteristics, aerodynamic forces, and performance comparisons are provided.
Date: May 6, 1953
Creator: Braden, John A. & Pierpont, P. Kenneth
Partner: UNT Libraries Government Documents Department

Flight tests of a delta-wing vertically rising airplane model powered by a ducted fan

Description: Report presenting the results of an investigation to determine the dynamic stability and control characteristics of a delta-wing vertically rising airplane model powered by a ducted fan. The model had flap-type control surfaces on the wings and vertical tail as well as movable eyelids at the rear of the tail pipe and air bled from the main duct and exhausted through movable nozzles near the wing tips. The model was found to generally fly smoothly and easily without automatic stabilization devices.
Date: April 6, 1955
Creator: Lovell, Powell M., Jr.
Partner: UNT Libraries Government Documents Department

Fuselage pressures measured on the Bell X-1 research airplane in transonic flight

Description: Report presenting pressure-distribution measurements on the fuselage of the Bell X-1 research airplane. A variety of angles of attack and Mach numbers were tested. Results regarding pressure distribution and normal load are provided.
Date: November 6, 1953
Creator: Knapp, Ronald J.; Jordan, Gareth H. & Johnson, Wallace E.
Partner: UNT Libraries Government Documents Department

Free-spinning-tunnel investigation to determine the effect on spins and recoveries of wing leading-edge chord-extensions and drooped leading-edge flaps on scale models of two sweptback-wing fighter airplanes

Description: Report discussing an investigation to determine the effect of wing leading-edge chord-extensions and drooped leading-edge flaps on the spin and spin-recovery characteristics of models of two swept-wing fighter airplanes. The investigation included chord-extensions in the plane of the wing and chord-extensions deflected in combination with drooped leading-edge flaps. The chord extensions were not found to have an appreciable effect on spin or spin-recovery characteristics when installed in the plane of the wing.
Date: May 6, 1953
Creator: Wilson, Jack H. & Klinar, Walter J.
Partner: UNT Libraries Government Documents Department