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Tabulated Pressure Data for a Series of Controls on a 40 Deg Sweptback Wing at Mach Numbers of 1.61 and 2.01

Description: An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions.
Date: November 8, 1957
Creator: Lord, D. R.

Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90

Description: Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.

Wind tunnel investigation at high subsonic speeds of drag at 0 degrees angle of attack of swept-wing fuselage models with pylon mounted and semisubmerged missiles

Description: Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date: October 8, 1956
Creator: King, Thomas J., Jr.

Characteristics of perforated diffusers at free-stream Mach number 1.90

Description: An investigation was conducted at Mach number 1.90 to determine pressure recovery and mass-flow characteristics of series of perforated convergent-divergent supersonic diffusers. Pressure recoveries as high as 96 percent were obtained, but at reduced mass flows through the diffuser. Theoretical considerations of effect of perforation distribution on shock stability in converging section of diffuser are presented and correlated with experimental data. A method of estimating relative importance of pressure recovery and mass flow on internal thrust coefficient basis is given and a comparison of various diffusers investigated is made.
Date: May 8, 1950
Creator: Hunczak, Henry R & Kremzier, Emil J