Three-dimensional viscous flow computations are presented for the F/A-18 forebody including the leading-edge extension geometry. Solutions are obtained from an algorithm for the compressible Navier-Stokes equations that incorporates an upwind-biased, flux-difference-splitting approach along with longitudinally patched grids. Results are presented for both laminar and fully turbulent flow assumptions and include correlations with wind-tunnel as well as flight-test results. A good quantitative agreement for the forebody surface pressure distribution is achieved between the turbulent computations and wind-tunnel measurements at M∞ = 0.6. The computed turbulent surface flow patterns on the forebody qualitatively agree well with in-flight surface flow patterns obtained on an F/A-18 aircraft at M∞ = 0.34
Navier-Stokes Solutions About the F/A-18 Forebody-Leading-Edge Extension Configuration
27th Aerospace Sciences Meeting ; 1989 ; Reno, NV, US
Journal of Aircraft ; 27 , 9
1990-09-01
Miscellaneous
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English