Supersonic Inlet Investigation
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Author | : Abraham Leiss |
Publisher | : |
Total Pages | : 50 |
Release | : 1958 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
A method is presented to design a supersonic inlet that will match turbojet-engine air mass-flow requirements over a wide Mach number range. Two types of bypasses were investigated; one had a 360 degree annular cowling and the other had twin slotted ducts. Three models were flight tested. Two of the models, which had bypass ducts, were also ground tested. The bypass models had higher external drags. Both bypass models approximated a typical turbojet-engine air mass-flow requirement between Mach numbers 1.0 and 2.0. The flight tests covered a Reynolds number range from 200,000 to 800,000 and a Mach number range from 0.8 to 1.95.
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 | : Antonio Ferri |
Publisher | : |
Total Pages | : 38 |
Release | : 1946 |
Genre | : |
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 | : Akira Fujimoto |
Publisher | : |
Total Pages | : |
Release | : 1991 |
Genre | : |
ISBN | : |
Author | : Donald P. Hearth |
Publisher | : |
Total Pages | : 52 |
Release | : 1956 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height relative to the boundary-layer thickness. The pressure recovery increased at about the same rate as theoretically predicted for an inlet in a boundary layer having a one-seventh power profile, but was only about 0.68 to 0.75 of the theoretically obtainable values. Under some operating conditions, flow from the primary jet was exhausted through the auxiliary inlet. This phenomenon could be predicted from the ejector pumping characteristics.
Author | : Clarence W. Matthews |
Publisher | : |
Total Pages | : 44 |
Release | : 1971 |
Genre | : Automatic control |
ISBN | : |
Author | : Nasim F. Amin |
Publisher | : |
Total Pages | : 366 |
Release | : 1971 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
A one-dimensional mathematical dynamic simulation model for predicting the transient behavior of air induction systems for advanced tactical aircraft operating in the supersonic portion of the flight spectrum is discussed. As a part of the simulation model, control system logic is included to provide control system design criteria necessary to maintain air induction system response to selected input disturbances within prescribed limits. The model is applicable to both external and mixed compression inlets operating at supersonic conditions. The 'lumped parameter' concept is used in simulating the dynamic response of the subsonic duct downstream of the terminal shock, with the duct divided into three lumps.
Author | : Junji Shigematsu |
Publisher | : |
Total Pages | : |
Release | : 1990 |
Genre | : |
ISBN | : |