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Aerodynamic validation of a SCAR designWind tunnel test of the McDonnell Douglas Supersonic Cruise Aircraft, designed for a cruise Mach number of 2.2, was conducted in the NASA Ames Unitary Plan Wind Tunnels. Extensive force, pressure, and flow visualization data were obtained over a Mach number range from 0.5 to 2.4. Comparisons between theory and measurements of both forces and pressure concentrate on the results obtained in the supersonic tunnel. Schlieren and tuft pictures are presented to help provide an understanding of the nonlinearities observed at off-design conditions.
Document ID
19770011061
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Roensch, R. L. (McDonnell-Douglas Corp. Saint Louis, MO, United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Publication Information
Publication: NASA. Langley Res. Center Proc. of the Scar Conf., Part 1
Subject Category
Aerodynamics
Accession Number
77N18005
Funding Number(s)
CONTRACT_GRANT: NAS1-13633
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19770011052Collected WorksProceedings of the SCAR Conference, Part 1
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