Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 PDF Download
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Author: John H. Lundell
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 38
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Author: John H. Lundell
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 38
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Book Description
Author: John H. Lundell
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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An idealized axisymmetric, all-internal compression inlet was designed for a Mach number of 3.75. The objective of the design was to obtain a steady, one-dimensional transonic flow and a high over-all total-pressure recovery. Boundary-layer removal was employed in the vicinity of the inflection point of the supersonic contour. Static- and total-pressure fluctuations were measured in the transonic flow region. A total-pressure recovery of about 90 percent was obtained with a boundary-layerremoval mass-flow rate of 15 percent of the inlet mass-flow rate. The accompanying root-meansquare total-pressure fluctuation in the throat region was only 1 percent of the free-stream total pressure. The test Mach number was 3.80 and the Reynolds number based on inlet diameter was 2.63 times 10 to the 6th power. (Author).
Author: Owen H. Davis
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 252
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Author: John L. Allen
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24
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Author: Bernhard H. Anderson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
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Author:
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ISBN:
Category :
Languages : en
Pages : 32
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Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 162
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Author: Earl C. Watson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 62
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Author: Leroy L. Presley
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 58
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