Development of Atmospheric Gust Criteria for Supersonic Inlet Design PDF Download
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Author: F. W. Barry
Publisher:
ISBN:
Category :
Languages : en
Pages : 212
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Author: F. W. Barry
Publisher:
ISBN:
Category :
Languages : en
Pages : 212
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Book Description
Author: Frank W. Barry
Publisher:
ISBN:
Category :
Languages : en
Pages : 7
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 736
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Author: Bruce Lehtinen
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Design and characteristics of supersonic inlet controls for minimizing inlet unstarts.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 610
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Author: Abraham Leiss
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 50
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Book Description
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:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 308
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Author:
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 100
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Author: T. W. Tsukahira
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 904
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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: I. H. Rettie
Publisher:
ISBN:
Category :
Languages : en
Pages :
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