Wind Tunnel Tests Of Supersonic Two Dimensional And Half Axisymmetric Inlet Models In A Nonuniform Flow Field At Mach Numbers From 15 Through 25
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Author | : Frederick K. Hube |
Publisher | : |
Total Pages | : 274 |
Release | : 1971 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Frederick K. Hube |
Publisher | : |
Total Pages | : 0 |
Release | : 1971 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Frederick K. Hube |
Publisher | : |
Total Pages | : 278 |
Release | : 1970 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Frederick K. Hube |
Publisher | : |
Total Pages | : 0 |
Release | : 1970 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : T. W. Tsukahira |
Publisher | : |
Total Pages | : 330 |
Release | : 1971 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
Author | : Tatsuo W. Tsukahira |
Publisher | : |
Total Pages | : 159 |
Release | : 1971 |
Genre | : |
ISBN | : |
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately .125 scale model air induction systems. The baseline models included a two-dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers. (Author).
Author | : T. W. Tsukahira |
Publisher | : |
Total Pages | : 904 |
Release | : 1971 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Reported herein are the results of an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests. The baseline models included a two-dimensional external compression inlet, a two-dimensional mixed compression inlet, and a half-axisymmetric external compression inlet. Alternate configurations for the external compression baseline inlets in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a non-uniform flow field, the later representing partial simulation of a vehicle flow field. Inlet steady state performance was characterized in terms of pressure recovery, pressure distortion, and turbulence levels at a simulated compressor face and immediately downstream of the inlet throat. In addition, detailed analysis and correlation of data obtained with high response dynamic instrumentation were made.
Author | : |
Publisher | : |
Total Pages | : 26 |
Release | : 2001 |
Genre | : |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 1466 |
Release | : 1966 |
Genre | : Aeronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 666 |
Release | : 2008 |
Genre | : Airplanes |
ISBN | : |