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Experimental Pressure Distribution on Fuselage Nose and Pilot Canopy of Supersonic Airplane at Mach Number 1.90

Description: An investigation of the pressure distribution on the fuselage nose and the pilot canopy of a supersonic airplane model has been conducted at a Mach number of 1.90 over a wide range of angles of attack and yaw. Boundary layer separation apparently occurred from the upper surface at angles of attack above 24 degrees and from the lower surface at minus 15 degrees. No separation from the sides of the fuselage was evident at yaw angles up to 12 degrees.
Date: October 15, 1948
Creator: Wyatt, DeMarquis D.
Partner: UNT Libraries Government Documents Department

Experimental pressure distribution on a asymmetrical nonconical body at Mach number 1.90

Description: Report presenting an investigation of the pressure distribution on an asymmetrical nonconical body at a Mach number of 1.90 over a wide range of angles of attack and yaw. Pressure distributions occurred at anticipated trends. Results regarding the pressure coefficients, Schileren photographs, boundary layers, and pressure distributions are provided.
Date: February 24, 1949
Creator: Wyatt, DeMarquis D.
Partner: UNT Libraries Government Documents Department

Investigation of a variable Mach number supersonic tunnel with nonintersecting characteristics

Description: Report presenting a method for the design of supersonic-wind-tunnel nozzles that produce uniform flow over a continuously variable Mach number range without the use of flexible walls. Experimental results from a preliminary investigation of the tunnel are included, including calibration survey of flow, Mach number distributions, and pressure gradients are provided.
Date: November 15, 1948
Creator: Evvard, John C. & Wyatt, DeMarquis D.
Partner: UNT Libraries Government Documents Department

Theoretical Performance Characteristics of Sharp Lip Inlets at Subsonic Speeds

Description: A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet pressure recovery - mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result.
Date: September 1953
Creator: Fradenburgh, Evan A. & Wyatt, DeMarquis D.
Partner: UNT Libraries Government Documents Department

Theoretical performance characteristics of sharp-lip inlets at subsonic speeds

Description: A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet-pressure-recovery mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result.
Date: 1954
Creator: Fradenburgh, Evan A. & Wyatt, DeMarquis D.
Partner: UNT Libraries Government Documents Department

An investigation of convergent-divergent diffusers at Mach number 1.85

Description: Report presenting an investigation in the supersonic tunnel at Mach number 1.85 and angles of attack from 0 to 5 degrees to determine optimum design configurations for a convergent-divergent type of supersonic diffusers with a subsonic diffuser of 5 degrees included divergence angle. Total-pressure recoveries in excess of the theoretical recovery across a normal shock at a free-stream Mach number of 1.85 were obtained with a number of configurations.
Date: February 2, 1951
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department

An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85

Description: An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations.
Date: April 28, 1947
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department

An investigation of cowl-flap and cowl-outlet designs for the Boeing B-29 power-plant installation

Description: Report discussing an investigation into cowl-flap and cowl-outlet designs for the B-29 in order to determine the effects of cowling performance of different types of flaps and elements of flaps. Details of the available pressure drop and cooling-air pressure-drop distribution are also provided.
Date: January 1946
Creator: Wyatt, DeMarquis D. & Conrad, E. William
Partner: UNT Libraries Government Documents Department