An Experimental Investigation of the Flow in an Axisymmetric Internal-compression Inlet for M PDF Download
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Author: Earl C. Watson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 62
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Author: Earl C. Watson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 62
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 392
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Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Military art and science
Languages : en
Pages : 1746
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 450
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Author: Norman D. Wong
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 68
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A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 104
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Author: Warren E. Anderson
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 68
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 244
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