180 Matching Results

Search Results

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

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

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

Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20

Description: Report presenting lift and drag data obtained during the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift. A comparison of the flight data with data from wind-tunnel and rocket-model tests shows that the model tests adequately predict the performance of the airplane.
Date: December 6, 1954
Creator: Bellman, Donald R. & Murphy, Edward D.
Partner: UNT Libraries Government Documents Department

Low-speed wind-tunnel investigation of a thin 60 degree delta wing with double slotted, single slotted, plain, and split flaps

Description: Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a thin delta wing equipped with various arrangements of double slotted, single slotted, plain, and split flaps. The wing was a flat plate with beveled leading and trailing edges and had a maximum thickness ratio of 0.045, and 60 degrees sweepback of the leading edge.
Date: January 6, 1953
Creator: Riebe, John M. & MacLeod, Richard G.
Partner: UNT Libraries Government Documents Department

The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing

Description: "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).
Date: December 6, 1948
Creator: Spearman, M. Leroy & Becht, Robert E.
Partner: UNT Libraries Government Documents Department

Investigation of a 10-stage subsonic axial-flow research compressor 4: performance evaluation and flow distributions in the first, fifth, and tenth stages

Description: Report presenting a determination of the performance and flow distributions in the first, fifth, and tenth stages of a 10-stage axial-flow research compressor at design and part speed in order to study the validity of the compressor design assumptions and to show the effects of part-speed compressor operation on stage performance.
Date: August 6, 1954
Creator: Budinger, Ray E.
Partner: UNT Libraries Government Documents Department

Effect of fuel properties on carbon deposition in atomizing and prevaporizing turbojet combustors

Description: Report presenting investigations of the effects of fuel properties on combustion-chamber carbon deposition in singe tubular fuel-atomizing and fuel-prevaporizing combustors. The NACA K factor and the smoking tendency were approximately equally effective in relating carbon-deposition data from the prevaporizing and atomizing combustors. Results regarding the K factor, smoking tendency, effect of prevaporizing combustor operating conditions, sulfur, gum, and olefin, are provided.
Date: June 6, 1952
Creator: Wear, Jerrold D. & Cook, William P.
Partner: UNT Libraries Government Documents Department

Effect of channel geometry on the quenching of laminar flames

Description: Report presenting the effect of channel geometry on flame quenching, as calculated on the basis of average active particle chain lengths, is related among six different geometries: plane parallel plates of infinite extent, cylindrical tubes, rectangular slots, cylindrical annuli, and tubes of elliptical and equilaterally triangular shape. The results indicated that the observed variation of flame quenching as a function of quenching geometry may be successfully predicted for a range of pressures and for rich as well as lean propane-air flames.
Date: May 6, 1954
Creator: Berlad, A. L. & Potter, A. E., Jr.
Partner: UNT Libraries Government Documents Department

Altitude performance investigation of two flame-holder and fuel-system configurations in short afterburner

Description: From Introduction: "The results of this complete evaluation of the altitude performance and operational characteristics of the two types of flame-holder and fuel-system configurations are reported herein.The starting limits of both configurations at a flight Mach number of 0.6 are also discussed."
Date: May 6, 1952
Creator: Huntley, S. C. & Wilsted, H. D.
Partner: UNT Libraries Government Documents Department