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Unsteady aerodynamic loads on slender cones at free-stream Mach numbers from 0 to 22.Results of an experimental study to determine the flow-induced unsteady aerodynamic loads on slender cones at very high Mach numbers. Experiments on 8-deg half-angle-cone/flat-base configurations were conducted at free-stream Mach numbers of 6 and 15 and Reynolds numbers corresponding to shuttle reentry conditions. The flow facilities used were the H-3 Hypersonic Facility (Mach 6) and the Longshot Free Piston Tunnel (Mach 15) of the Von Karman Institute for Fluid Dynamics in Rhode-St.-Genese, Belgium. With these test results and pertinent results from other research efforts, data were available at free-stream Mach numbers of 0.67, 2.5, 3, 4, 6, 15, and 22, so that empirical expressions could be developed for the Mach number dependence (1) of the overall fluctuating pressure under an attached turbulence boundary layer and (2) of the overall fluctuating base pressure.
Document ID
19730060031
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Heller, H. H.
Clemente, A. R.
(Bolt Beranek and Newman, Inc. Cambridge, Mass., United States)
Date Acquired
August 7, 2013
Publication Date
October 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 73-998
Meeting Information
Meeting: Aero-Acoustics Conference
Location: Seattle, WA
Start Date: October 15, 1973
End Date: October 17, 1973
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
73A44833
Distribution Limits
Public
Copyright
Other

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