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The effect of some surface roughness elements on the drag of a body of revolution at supersonic speeds

Description: From Summary: "The effects of some rivets, butt joints, and lap joints on the drag of a body of revolution at zero lift at supersonic Mach numbers to 2.1 have been obtained in free flight with rocket-propelled models. The butt joints tested showed no significant effects on the drag. Rivets and lap joints increased the drag of the smooth-body configuration, the forward-facing lap joints contributing the greatest increases."
Date: November 24, 1954
Creator: Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at high subsonic speeds of the effects of wing-mounted external stores on the loading and aerodynamic characteristics in pitch of a 45 degree sweptback wing combined with a fuselage

Description: Report presenting an investigation of the effect of wing-mounted external stores on the loading and aerodynamic characteristics in pitch of a 45 degree sweptback wing combined with a fuselage. Store arrangements investigated consisted of stores mounted at the wing tips, stores mounted inboard on the wing undersurface at 46-percent semispan, and stores in both the tip and inboard locations.
Date: March 23, 1954
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Effect of mechanically induced sinusoidal air-foil oscillations on operation of a ram-jet engine

Description: Report presenting an experimental investigation in a 16-inch ram-jet engine to examine the degree to which inlet flow pulsations influence the combustion efficiency and lean blow-out limit of a ram-jet combustor.
Date: June 16, 1954
Creator: Dangle, E. E.; Cervenka, A. J. & Perchonok, Eugene
Partner: UNT Libraries Government Documents Department

Rotating-stall and rotor-blade-vibration survey of a 13-stage axial-flow compressor in a turbojet engine

Description: Report presenting a blade-vibration and rotating-stall survey on a production turbojet engine with a 13-stage axial-flow compressor with a pressure ratio of 7 and an air flow of 120 pounds per second. Results regarding stall patterns, maximum vibratory stresses, and location of the stall zones are provided.
Date: April 29, 1955
Creator: Calvert, Howard F.; Braithwaite, Willis M. & Medeiros, Arthur A.
Partner: UNT Libraries Government Documents Department

Flight test of a radial-burning solid-fuel ram jet

Description: Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.
Date: December 10, 1952
Creator: Bartlett, Walter A., Jr. & Dettwyler, H. Rudolph
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the total-pressure-recovery characteristics of a 15 degree semiangle movable-cone variable-geometry ram-jet inlet at free-jet Mach numbers of 1.62, 2.00, 2.53, and 3.05

Description: Report presenting an investigation of a 15 degree semiangle movable-cone variable-geometry ram-jet inlet to determine the variable-geometry effect on total-pressure recovery at free-jet Mach numbers of 1.62, 2.00, 2.53, and 3.05 at zero angles of attack and yaw. Generally, increasing the cowling-position parameter increased the value of both total-pressure recovery and mass-flow ratio. Results regarding the total-pressure recovery, shadowgraphs, and total-pressure recovery as a function of free-stream Mach number are provided.
Date: January 8, 1953
Creator: Hinners, Arthur H., Jr. & Lee, John B.
Partner: UNT Libraries Government Documents Department

Some control considerations for ram-jet engines / c Seymour Himmel

Description: Control requirements were determined from calculated engine performance maps for a fixed-geometry ram jet of a configuration suitable for strategic supersonic missile propulsion. Several control schemes for attaining desired engine performance and for stabilizing missile flight velocity during cruise are presented. The advantages and disadvantages of each system are discussed.
Date: August 11, 1952
Creator: Himmel, Seymour C
Partner: UNT Libraries Government Documents Department