Numerical simulation of the viscous flow around a simplified F/A-18 at high angles of attackA numerical method developed for solving the viscous flow around three-dimensional complex configurations is presently used to simulate the flow around a simplified F/A-18 configuration encompassing forebody, wing, leading-edge extension, faired-over inlet, and deflected wing leading-edge flaps, at Mach 0.243 and 30.3 deg angle of attack. The computational results show the details of the flowfield structure, including primary, secondary, and tertiary separation lines, the development of forebody and leading-edge extension vortex, and the burst of this vortex. A grid-refinement study is conducted to assess the effect of grid characteristics on solution accuracy. Substantial agreement is obtained between these results and flight data.
Document ID
19900058794
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rizk, Yehia M. (NASA Ames Research Center Moffett Field, CA, United States)
Schiff, Lewis B. (NASA Ames Research Center Moffett Field, CA, United States)
Gee, Ken (NASA Ames Research Center Moffett Field, CA, United States)