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Adaptive computations of flow around a delta wing with vortex breakdownAn adaptive unstructured mesh solution method for the three-dimensional Euler equations was used to simulate the flow around a sharp edged delta wing. Emphasis was on the breakdown of the leading edge vortex at high angle of attack. Large values of entropy, which indicate vortical regions of the flow, specified the region in which adaptation was performed. The aerodynamic normal force coefficients show excellent agreement with wind tunnel data measured by Jarrah, and demonstrate the importance of adaptation in obtaining an accurate solution. The pitching moment coefficient and the location of vortex breakdown are compared with experimental data measured by Hummel and Srinivasan, showing good agreement in cases in which vortex breakdown is located over the wing.
Document ID
19930063205
Document Type
Conference Paper
Authors
Modiano, David L. (MIT, Cambridge, MA; NASA, Lewis Research Center Cleveland, OH, United States)
Murman, Earll M. (MIT Cambridge, MA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Applied Aerodynamics Conference, 11th, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-47201 19-02)
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 93-3400
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-89-0395A
Distribution Limits
Public
Copyright
Other