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Investigation of boattail and base pressures of twin-jet afterbodies at Mach number 1.91

Description: Report presenting an investigation of the boattail pressures and base pressures of two twin-jet afterbody configurations at Mach number 1.91. They were designed as a simple merging of two blunt-based conical afterbodies with spacings of 1.4 and 1.7 jet diameters between the jet center lines. Results regarding support-strut interference, effect of jet spacing ratio, effect of jet exit angle, longitudinal boattail pressure distribution, circumferential pressure distributions, and effect of a reflection plane are provided.
Date: April 21, 1955
Creator: Salmi, Reino J. & Klann, John L.
Partner: UNT Libraries Government Documents Department

Interference effects at Mach 1.9 on a horizontal tail due to trailing shock waves from an axisymmetric body with an exiting jet

Description: Report presenting measurements of the normal force and pitching moment of a rectangular tail surface at Mach 1.9 to determine the interference effects due to trailing shock waves from an axisymmetric body with a jet exiting from a sonic nozzle in the base. The data were obtained at various jet pressure ratios and locations of tail with respect to the body. Results regarding tail location, tail pitching moment, and tail-shock-wave effects on base pressure are provided.
Date: January 25, 1956
Creator: Salmi, Reino J. & Klann, John L.
Partner: UNT Libraries Government Documents Department

Experimental investigation of interference effects of lateral-support struts on afterbody pressures at Mach 1.9

Description: Report presenting testing of a series of single and double unswept, lateral-support struts at a Mach number of 1.9 on a cone-cylinder body at zero angle of attack. The struts consisted of a rectangular box section with identical wedge fairings fore and aft. Results regarding the shock-wave intersections and pressure distributions are provided.
Date: May 14, 1956
Creator: Klann, John L. & Huff, Ronald G.
Partner: UNT Libraries Government Documents Department

Experimental investigation of methods of improving diffuser-exit total-pressure profiles for side-inlet model at Mach number 3.05

Description: Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.
Date: August 29, 1955
Creator: Piercy, Thomas G. & 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

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