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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

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

The design of brittle-material blade roots based on theory and rupture tests of plastic models

Description: From Summary: "Theoretical design charts based on Neuber's equations for symmetrically located notches are presented for estimating the approximate rupture strengths of blade roots made from brittle materials. The limit of applicability of the theoretical charts is shown as determined by rupture tests of plastic models. The optimum proportions among over-all root width, neck width, notch radius, and notch depth are determined from the design charts."
Date: April 6, 1953
Creator: Meyer, André J., Jr.; Kaufman, Albert & Caywood, William C.
Partner: UNT Libraries Government Documents Department

Analysis of limitations imposed on one-spool turboprop-engine designs by compressors and turbines at flight mach numbers of 0.06, and 0.8

Description: Turbine centrifugal stress is a limiting factor for all flight conditions studied. This stress is more severe for sea-level operations than for subsonic flight at the tropopause. Turbines designed for a stress of 30,000 psi are capable of driving a light, compact, high-spedd compressor but only at high values of specific fuel consumption. An increase in turbine-inlet temperature is accompanied by an increase in turbine centrifugal stress. If stresses in excess of 50,000 psi can be tolerated, compressor aerodynamics may become a primary limitation.
Date: December 6, 1956
Creator: Cavicchi, Richard H
Partner: UNT Libraries Government Documents Department

A simplified method for evaluating jet-propulsion-system components in terms of airplane performance

Description: Report presenting a method to provide a simple means of comparing engine components on the basis of either range or the margin of thrust over drag. The equations include the variation in thrust coefficient and specific impulse and the change in engine weight and drag. Four general cases are considered: fixed-size airplanes with constant gross weight, fixed-size airplanes with variable gross weight, variable-size airplanes with constant payload weight, and variable-size airplanes with constant ratio of payload to gross weight.
Date: December 6, 1956
Creator: Weber, Richard J. & Luidens, Roger W.
Partner: UNT Libraries Government Documents Department

Effects of leading-edge chord extensions and an all-movable horizontal tail on the aerodynamic characteristics of a wing-body combination employing a triangular wing of aspect ratio 3 mounted in a high position at subsonic and supersonic speeds

Description: Report presenting the results of an experimental investigation of the effect of leading-edge chord extensions on the aerodynamic characteristics of a wing-body-tail combination employing a 3-percent-thick triangular wing of aspect ratio 3 in conjunction with an unswept, all-movable, horizontal tail located below the wing-chord plane. Lift, drag, pitching moment, and hinge moment were measured a range of Mach numbers and a constant Reynolds number.
Date: January 6, 1954
Creator: Wetzel, Benton E. & Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department

Experimental and theoretical study of the interference at low speed between slender bodies and triangular wings

Description: Report presenting the aerodynamic characteristics of several wing-fuselage combinations measured at a Mach number of 0.25. Each combination consisted of a triangular wing with an aspect ratio of 2.0 and body of revolution with a fineness ratio of 12.5. Results regarding wings in the presence of bodies, wing-body combinations, and dorsal fins are provided.
Date: May 6, 1953
Creator: Hopkins, Edward J. & Carel, Hubert C.
Partner: UNT Libraries Government Documents Department

Experimental investigation of internal flow characteristics of forward underslung fuselage scoops with unswept entrances at Mach numbers of 1.41 to 1.96

Description: Report presenting an investigation of two versions of a type of forward underslung scoop mounted on a pointed fuselage in the supersonic blowdown tunnel. The scoop entrances were in the shape of a 60 degree sector of an annulus, but the sides of one scoop were sweptback, while the others were unswept. Results regarding the shadowgraphs and surface-pressure distributions and total-pressure recovery are provided.
Date: March 6, 1952
Creator: Boswinkle, Robert W., Jr. & Mitchell, Meade H., Jr.
Partner: UNT Libraries Government Documents Department

A study of fuel-nitric acid reactivity

Description: Report presenting a determination of the relative reactivities of six fuels with red fuming nitric acid in a 40-pound-thrust rocket engine with rapid liquid-phase mixing. Hydrazine, trimethyl-trithiophosphite, furfuryl alcohol, unsymmetrical dimethylhydrazine, allylamine, and o-toluidine were studied. Results regarding the combustion characteristics of the fuels, fuel ratings, pressure in the mixing cup, effect of chamber diameter, and overall combustion efficiency are provided.
Date: April 6, 1956
Creator: Feiler, Charles E. & Baker, Louis, Jr.
Partner: UNT Libraries Government Documents Department

Results of preliminary flight tests of the XS-1 airplane (8-percent wing) to a Mach number of 1.25

Description: Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Date: April 6, 1948
Creator: Williams, W. C. & Beeler, De E.
Partner: UNT Libraries Government Documents Department