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Computation of supersonic turbulent flow past a spinning coneComputational results are presented for supersonic laminar and turbulent flow past a pointed cone at angle of attack obtained with a parabolic Navier-Stokes marching code. The code takes into account the asymmetries in the flowfield 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 analyses based on boundary-layer equations. For certain laminar flow conditions, an anomaly is discovered in the displacement thickness contribution to the Magnus force when compared with boundary-layer results. For turbulent flow, at small angles of attack, good agreement is obtained with the experimental data and other theoretical results.
Document ID
19820038553
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Agarwal, R. K.
(McDonnell Douglas Research Laboratories St. Louis, MO, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 82-0304
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Orlando, FL
Start Date: January 11, 1982
End Date: January 14, 1982
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
82A22088
Distribution Limits
Public
Copyright
Other

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