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Comparison of measured and computed pitot pressures in a leading edge vortex from a delta wingCalculations are presented for a 75-deg swept flat plate wing tested at a freestream Mach number of 1.95 and 10 degrees angle of attack. Good agreement is found between computational data and previous experimental pitot pressure measurements in the core of the vortex, suggesting that the total pressure losses predicted by the Euler equation solvers are not errors, but realistic predictions. Data suggest that the magnitude of the total pressure loss is related to the circumferential velocity field through the vortex, and that it increases with angle of attack and varies with Mach number and sweep angle.
Document ID
19870054238
Document Type
Conference Paper
Authors
Murman, Earll M. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Powell, Kenneth G. (MIT Cambridge, MA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
AERODYNAMICS
Funding Number(s)
CONTRACT_GRANT: NAG1-358
Distribution Limits
Public
Copyright
Other