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Interactive calculation procedures for mixed compression inletsThe proper design of engine nacelle installations for supersonic aircraft depends on a sophisticated understanding of the interactions between the boundary layers and the bounding external flows. The successful operation of mixed external-internal compression inlets depends significantly on the ability to closely control the operation of the internal compression portion of the inlet. This portion of the inlet is one where compression is achieved by multiple reflection of oblique shock waves and weak compression waves in a converging internal flow passage. However weak these shocks and waves may seem gas-dynamically, they are of sufficient strength to separate a laminar boundary layer and generally even strong enough for separation or incipient separation of the turbulent boundary layers. An understanding was developed of the viscous-inviscid interactions and of the shock wave boundary layer interactions and reflections.
Document ID
19900016618
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Reshotko, Eli (Case Inst. of Tech. Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-186581
NAS 1.26:186581
Accession Number
90N25934
Funding Number(s)
CONTRACT_GRANT: NAG3-140
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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