Numerical simulation of high-incidence flow over the F-18 aircraftNavier-Stokes solutions have been obtained using the Chimera overset grid scheme for flow over the wing, fuselage, and wing leading-edge extension (LEX) of the F-18 aircraft at high incidence. Solutions are also presented for flow over the fuselage forebody at high angles of attack. The solutions are for turbulent flows at high-Reynolds number flight-test conditions, and are compared with available qualitative and quantitative experimental data. Comparisons of predicted surface flow patterns, off-surface flow visualizations, and surface-pressure distributions are in good agreement with flight-test data. The ability of the numerical method to predict the bursting of the LEX vortex as it encounters the adverse pressure gradient field of the wing is demonstrated.
Document ID
19910039730
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cummings, Russell M. (NASA Ames Research Center Moffett Field, CA, United States)
Schiff, Lewis B. (NASA Ames Research Center Moffett Field, CA, United States)
Rizk, Yehia M. (NASA Ames Research Center Moffett Field, CA, United States)
Chaderjian, Neal M. (NASA Ames Research Center Moffett Field, CA, United States)