NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Hypersonic Laminar Viscous Flow Past Spinning Cones at Angle of AttackComputational results are presented for hypersonic viscous flow past spinning sharp and blunt cones of 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, cross-flow and streamwise shear, heat transfer, cross-flow 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.
Document ID
19990026883
Acquisition Source
Ames Research Center
Document Type
Reprint (Version printed in journal)
Authors
Agarwal, Ramesh
(National Academy of Sciences - National Research Council Moffett Field, CA United States)
Rakich, John V.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 19, 2013
Publication Date
April 1, 1982
Publication Information
Publication: AIAA Journal
Publisher: American Institute of Aeronautics and Astronautics
Volume: 20
Issue: 4
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA Paper 78-65R
Meeting Information
Meeting: Aerospace Sciences
Location: Huntsville, AL
Country: United States
Start Date: January 16, 1978
End Date: January 18, 1978
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.
No Preview Available