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Experimental and computational study of transonic flow about swept wingsAn experimental investigation of NACA 0010 and 10% circular arc wing models, swept at 45 deg, spanning a channel, and at zero angle of attack is described. Measurements include chordwise and spanwise surface pressure distributions and oil-flow patterns for a range of transonic Mach numbers and Reynolds numbers. Calculations using a new three-dimensional Navier-Stokes code and a two-equation turbulence model are included for the circular-arc wing flow. Reasonable agreement between measurements and computations is obtained.
Document ID
19800034065
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bertelrud, A. (NASA Ames Research Center Moffett Field, CA, United States)
Bergmann, M. Y. (NASA Ames Research Center Moffett Field, CA, United States)
Coakley, T. J. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-0005
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Pasadena, CA
Start Date: January 14, 1980
End Date: January 16, 1980
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
80A18235
Distribution Limits
Public
Copyright
Other

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