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Computation of hypersonic laminar viscous flow past spinning sharp and blunt cones at high angle of attackComputational results, obtained with a parabolic Navier-Stokes marching code, are presented for hypersonic viscous flow past spinning sharp and blunt cones at angle of attack. The code takes into account the asymmetries in the flow field resulting from spinning motion and computes the asymmetric shock shape, crossflow and streamwise shear, heat transfer, crossflow separation, and vortex structure. The Magnus force and moments are also computed. Comparisons are made with other theoretical analyses based on boundary-layer and boundary-region equations, and an anomaly is discovered in the displacement thickness contribution to the Magnus force when compared with boundary-layer results. In addition, a new criterion for defining crossflow separation behind spinning bodies is introduced which generalizes the Moore-Rott-Sears criterion for two-dimensional unsteady separation. A condition which characterizes the onset of separation in the flow field is defined.
Document ID
19780038653
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Agarwal, R.
(NASA Ames Research Center Moffett Field, CA, United States)
Rakich, J. V.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 78-65
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Huntsville, AL
Start Date: January 16, 1978
End Date: January 18, 1978
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
78A22562
Distribution Limits
Public
Copyright
Other

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