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Numerical solution of supersonic laminar flow over an inclined body of revolutionA mixed explicit-implicit scheme is used to solve the time-dependent thin-layer approximation of the Navier-Stokes equations for a supersonic laminar flow over an inclined body of revolution. Test cases for Mach 2.8 flow over a cylinder with 15 deg flare angle at angles of attack of 0, 1, and 4 deg are calculated. Good agreement is obtained between the present computed results and experimental measurements of surface pressure. A pair of vortices on the leeward and a peak in the normal force distribution near the flared juncture are predicted; the role of circumferential communication is discussed.
Document ID
19790062710
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hung, C. M. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-1547
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference
Location: Williamsburg, VA
Start Date: July 23, 1979
End Date: July 25, 1979
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
79A46723
Distribution Limits
Public
Copyright
Other

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