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Interaction between a supersonic stream and a parallel subsonic stream bounded by fluid at rest

Author: Herbert S Ribner; E Leonard Arnoff; United States. National Advisory Committee for Aeronautics.
Publisher: Washington, D.C. : National Advisory Committee for Aeronautics, 1952.
Series: Technical note (United States. National Advisory Committee for Aeronautics), no. 2860.
Edition/Format:   Book : National government publication : EnglishView all editions and formats
Database:WorldCat
Summary:
Tsien and Finston's simplified model of shock boundary-layer interaction is modified to introduce effects of the separated "dead-air" bubble, where one exists. The boundary layer is simulated by an inviscid uniform subsonic stream bounded below by fluid at rest and impinged on above by a week oblique shock in an infinite supersonic stream. Linearized analysis indicates that the simulated boundary layer approximates  Read more...
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Details

Material Type: Government publication, National government publication
Document Type: Book
All Authors / Contributors: Herbert S Ribner; E Leonard Arnoff; United States. National Advisory Committee for Aeronautics.
OCLC Number: 668455772
Notes: "December 1952."
NACA TN No. 2860.
Description: 45 p. : ill. ; 28 cm.
Series Title: Technical note (United States. National Advisory Committee for Aeronautics), no. 2860.
Responsibility: Herbert S. Ribner and E. Leonard Arnoff.

Abstract:

Tsien and Finston's simplified model of shock boundary-layer interaction is modified to introduce effects of the separated "dead-air" bubble, where one exists. The boundary layer is simulated by an inviscid uniform subsonic stream bounded below by fluid at rest and impinged on above by a week oblique shock in an infinite supersonic stream. Linearized analysis indicates that the simulated boundary layer approximates the expansive corner turn that would occur if the shock were incident directly on the dead-air region; there are localized distortions top and bottom.

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