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External-stream effects on gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers

Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the external-stream effects on the gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers. Results regarding the pumping, thrust, and base characteristics, boattail drag characteristics, and stream effects on jet thrust for typical ejector installations are provided.
Date: June 26, 1956
Creator: Valerino, Alfred S. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department

Investigation of control signals for variable ramps of twin-duct side inlets

Description: Report presenting an investigation in the supersonic wind tunnel to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct, side-inlet, fuselage forebody model of a prototype aircraft. These types of control systems have been found to be particularly helpful in supersonic flight. Results regarding inlet stability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, effect of angle of attack, and theoretical normal-shock-position control are provided.
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department

Investigation of control signals for variable ramps of twin-duct side inlets

Description: Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and theoretical normal-shock-position control are provided.
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department

Performance of twin-duct variable-geometry side inlets at mach numbers of 1.5 to 2.0

Description: Report presenting testing of the performance of a twin-duct air-intake system mounted on the sides of a 1/8-scale fuselage forebody model of a proposed aircraft at several Mach numbers, angles of attack, and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 and 30 degree second ramp angles, performance with fixed second-ramp angles, and effect of canards are provided.
Date: January 21, 1957
Creator: Yeager, Richard A.; Beheim, Milton A. & Klann, John L.
Partner: UNT Libraries Government Documents Department

Performance of twin-duct variable-geometry side inlets at Mach numbers of 1.5 to 2.0

Description: Report presenting testing of a twin-duct air-intake system mounted on the sides of a fuselage forebody model at free stream Mach numbers of 1.5 and 2.0 over angles of attack and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 degree and 30 degree second-ramp angles, performance with fixed second-ramp angles, and effect of canards are provided.
Date: January 21, 1957
Creator: Yeager, Richard A.; Beheim, Milton A. & Klann, John L.
Partner: UNT Libraries Government Documents Department