PN/S calculations for a fighter W/F at high-lift yaw conditionsThe NASA/Ames parabolized Navier/Stokes computer code was used to calculate the turbulent flow over the wing/fuselage for a generic fighter at M = 2.2. 18 deg angle-of-attack, and 0 and 5 deg yaw. Good test/theory agreement was achieved in the zero yaw case. No test data were available for the yaw case.
Document ID
19860064850
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wai, J. C. (Boeing Military Airplane Development Seattle, WA, United States)
Blom, G. (Boeing Military Airplane Development Seattle, WA, United States)
Yoshihara, H. (Boeing Military Airplane Co. Seattle, WA, United States)
Chaussee, D. (NASA Ames Research Center Moffett Field, CA, United States)