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Investigation at supersonic speeds of a translating-spike inlet employing a steep-lip cowl

Description: Report presenting an experimental investigation conducted in the supersonic wind tunnel at three Mach numbers on a translating-spike inlet analytically designed to keep the cone shoulder downstream of the cowl-lip station without a net internal contraction. The inlet in this investigation had an internal cowl-lip angle of 17.5 degrees and was constructed to have the same inlet capture area and maximum cross-sectional area as a previously tested inlet with an internal cowl-lip angle of only 7 degrees. Results regarding the total pressure recovery, effect of spike translation, external drag coefficients, and effective thrust parameter are provided.
Date: October 11, 1954
Creator: Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

Investigation of translating-spike supersonic inlet as means of mass-flow control at Mach numbers of 1.5, 1.8, and 2.0

Description: Report presenting an investigation in the supersonic wind tunnel on a 50 degree conical-spike inlet at three Mach numbers over a range of angles of attack. The additive-drag penalty associated with inlet mass-flow spillage was significantly reduced by using a translating-spike inlet rather than a fixed-geometry inlet.
Date: October 29, 1953
Creator: Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

Pumping and drag characteristics of an aircraft ejector at subsonic and supersonic speeds

Description: Report presenting an investigation in the supersonic wind tunnel on a cylindrical-shroud ejector. Data were obtained at several weight-flow ratios, primary pressure ratios, and free-stream Mach numbers. The results indicate that there was no effect of free-stream Mach number on the pumping characteristics of an ejector of this type. Results regarding the internal characteristics and external characteristics are provided.
Date: June 3, 1954
Creator: Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body

Description: Report presenting an investigation in the supersonic wind tunnel on an inlet employing conical flow separation from a probe extending upstream from a hemispherical-nosed centerbody. Pressure-recovery and drag characteristics for the inlet were very nearly comparable with a conical-spike inlet, but compared less favorably at Mach numbers below 2.0. A large reduction in pressure recovery and mass flow was obtained at angle of attack.
Date: January 19, 1953
Creator: Hearth, Donald P. & Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

Investigation of thrust and drag characteristics of a plug-type exhaust nozzle

Description: From Summary: "An investigation was conducted in the 8- by 6-foot supersonic wind tunnel on the external and internal characteristics of a plug-type exhaust nozzle. Two positions of the center plug, one simulating a convergent nozzle and the other a convergent-divergent nozzle, were investigated. Data were obtained at free-stream Mach numbers of 0.1, 0.6, 1.6, and 2.0 over a pressure-ratio range of 1 to 20 and angles of attack of zero and 8 degrees. Results of this investigation indicated that the plug nozzle had thrust-minus-drag performance over the entire pressure-ratio range comparable with equivalent conventional nozzles."
Date: February 19, 1954
Creator: Hearth, Donald P. & Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

Comparison at supersonic speeds of translating spike inlets having blunt- and sharp-lip cowls

Description: Report presenting an investigation of two translating spike inlets with blunt- and sharp-lip cowls in the supersonic wind tunnel at a range of free-stream Mach numbers and angles of attack. Results regarding the inlet stability, critical inlet performance at zero angle of attack, and inlet-engine matching are provided.
Date: January 19, 1954
Creator: Gorton, Gerald C. & Dryer, Murray
Partner: UNT Libraries Government Documents Department

Thrust characteristics of a series of convergent-divergent exhaust nozzles at subsonic and supersonic flight speeds

Description: From Summary: "An experimental investigation of a series of four convergent-divergent exhaust nozzles was conducted in the Lewis 8-by-6 foot supersonic wind tunnel at Mach numbers of 0.1, 0.6, 1.6, and 2.0 over a range of nozzle pressure ratios. The thrust characteristics of these nozzles were determined by a pressure-integration technique. From a thrust standpoint, a nozzle designed to give uniform parallel flow at the exit had no advantage over the simple geometric design with conical convergent and divergent sections."
Date: March 12, 1954
Creator: Fradenburgh, Evan A.; Gorton, Gerald C. & Beke, Andrew
Partner: UNT Libraries Government Documents Department