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Investigation of flutter characteristics of three low-aspect-ratio all-movable half-span control surfaces at Mach numbers from 1.49 to 2.87

Description: Report presenting the results of a supersonic flutter investigation of three low-aspect-ratio control surfaces, two which had all-movable controls and one with a fixed cutout. Experimental results are provided and compared to calculations using the piston theory for plan form 2. Modifications for improving the flutter of the various control surfaces are also described.
Date: May 2, 1958
Creator: Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of static- and base-pressure increases resulting from combustion of aluminum borohydride adjacent to body of revolution in supersonic wing tunnel

Description: Report presenting pressure distribution associated with the stable combustion of aluminum borohydride about a body of revolution in a wind tunnel at Mach number 2.47. Pressure increases on the cylindrical and base surfaces of the model were measured. Results regarding the burning and associated flow phenomena, axial and meridional static-pressure data obtained during combustion, and base-pressure data during combustion are provided.
Date: October 2, 1957
Creator: Serafini, John S.; Dorsch, Robert G. & Fletcher, Edward A.
Partner: UNT Libraries Government Documents Department

Flight measurements of the effects of surface condition on the supersonic drag of fin-stabilized parabolic bodies of revolution

Description: Report presenting testing of rocket-powered models at supersonic speeds to determine some of the surface conditions on the zero-lift drag of fin-stabilized parabolic bodies of revolution. Two types of models and three types of surface roughness were tested. Results regarding mean-drag coefficients, side-pressure coefficients, and total-drag coefficients are provided.
Date: May 2, 1952
Creator: Jackson, H. Herbert
Partner: UNT Libraries Government Documents Department

Investigation of jet effects on a flat surface downstream of the exit of a simulated turbojet nacelle at a free-stream Mach number of 1.39

Description: Report presenting an investigation utilizing a blowdown-type tunnel to determine the effects of a propulsive jet on a zero angle-of-attack wing surface located in the vicinity of both a choked convergent nozzle and a convergent-divergent nozzle. Static-pressure surveys were made on a flat surface located in the vicinity of the propulsive jet. Results regaridng the jet-off and jet-on pressure coefficients, shock waves, and incremental normal force are provided.
Date: April 2, 1956
Creator: Bressette, Walter E. & Leiss, Abraham
Partner: UNT Libraries Government Documents Department

Investigation of mechanical fastenings for solid turbine blades made from ductile materials

Description: Report presenting rupture testing conducted on tensile specimens of fir-tree turbine blade root fastenings for three specific turbojet engines. Testing was conducted at temperatures from 0 degrees to 1500 degrees. Results regarding the short-time tests at various temperatures, long-time stress-rupture tests at 1200 degrees Fahrenheit, long-time tests at increased temperature, and remarks on the criteria for using the fir-tree root design are provided.
Date: August 2, 1954
Creator: Meyer, André J., Jr.; Kaufman, Albert & Caywood, W. C.
Partner: UNT Libraries Government Documents Department

Nonmetallic Material Compatibility with Liquid Fluorine

Description: Static tests were made on the compatibility of liquid fluorine with several nonmetallic materials at -3200 F and at pressures of 0 and 1500 pounds per square inch gage. The results are compared with those from previous work with gaseous fluorine at the same pressures, but at atmospheric temperature. In general, although environmental effects were not always consistent, reactivity was least with the low-temperature, low-pressure liquid fluorine. Reactivity was greatest with the warm, high-pressure gaseous fluorine.
Date: October 2, 1957
Creator: Price, Harold G., Jr. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department

Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 with area suction applied to trailing-edge flaps and with several wing leading-edge modifications

Description: Report presenting an investigation of an airplane model conducted to determine the effect of area-suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. Results regarding the effect of trailing-edge flaps on the aerodynamic characteristics of the model with horizontal tail off, effect of wing modifications on the high-lift characteristics of the model with the horizontal tail off, aerodynamic characteristics of the model with the horizontal tail installed, and area-suction requirements are provided.
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Partner: UNT Libraries Government Documents Department

Longitudinal stability and drag characteristics at Mach numbers from 0.70 to 1.37 of rocket-propelled models having a modified triangular wing

Description: From Summary: "A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the root and 5.98 percent thick at the tip was designed in an attempt to improve the lift and drag characteristics of triangular wings. Free-flight drag and stability tests were made using rocket-propelled models equipped with the modified wing. The Mach number range of the test was from 0.70 to 1.37."
Date: May 2, 1952
Creator: Chapman, Rowe, Jr. & Morrow, John D.
Partner: UNT Libraries Government Documents Department

Fuselage side inlets : a study of some factors affecting their performance and a comparison with nose inlets

Description: Report presenting basic principles affecting the performance of side-inlet air-induction systems as well as an examination of the performance of several fuselage side inlets and a comparison with nose inlets. Methods for improving the performance of both types of inlets are reviewed.
Date: April 2, 1956
Creator: Mossman, Emmet A.; Pfyl, Frank A. & Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department

Comparison of Experimental Hydrodynamic Impact Loads and Motions for a V-Step and a Transverse-Step Hydro-Ski

Description: Report presenting a comparison of the hydrodynamic impact loads and motions encountered in testing a V-step and a transverse-step flat-bottom hydro-ski with beam loadings of about 4.5. Testing occurred in smooth water over a range of velocities, flight-path angles, and fixed trims. Results regarding time histories of draft, vertical velocity, and vertical acceleration, impact lift coefficient, draft coefficient, and time coefficient for rebound are provided.
Date: February 2, 1954
Creator: Miller, Robert W.
Partner: UNT Libraries Government Documents Department

Analysis of several methods of pumping cooling air for turbojet engine afterburners

Description: From Introduction: "Afterburning is well established as an effective means of increasing the thrust of a turbojet engine. In order to obtain the maximum thrust from an afterburner, it is necessary to burn to the highest temperatures possible (reference 1). At these high temperatures, material limitations (reference 2) necessitate the installation of cooling systems to permit safe and reliable operation."
Date: February 2, 1953
Creator: Samuels, John C. & Yanowitz, Herbert
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

Description: From Introduction: "The Ames Aeronautical Laboratory has in progress an experimental investigation of the aerodynamic characteristics of wings of interest in the design of high-speed fighter aircraft. This program included an investigation in the Ames 6-by 6-foot supersonic wind tunnel at both subsonic and supersonic Mach numbers of a wing-body combination having a 3-percent-thick, unswept, tapered wing with circular-arc sections and an aspect ratio of 3.1 (reference 1).
Date: May 2, 1952
Creator: Emerson, Horace F. & Gale, Bernard M.
Partner: UNT Libraries Government Documents Department

Analysis of effects of airplane characteristics and autopilot parameters on a roll-command system with aileron rate and deflection limiting

Description: From Summary: "The dynamic characteristics of an airplane with a proportional-gain roll-control autopilot are discussed. A comparison of three different high-speed fighter airplanes is presented. The dynamic effects of time lags and various gains in the system are described."
Date: September 2, 1955
Creator: Schy, Albert A. & Gates, Ordway B., Jr.
Partner: UNT Libraries Government Documents Department