Three-dimensional thin-layer Navier-Stokes computations are presented for the F/A-18 configuration. The modeled configuration includes an accurate surface representation of the fuselage, leading-edge extension (LEX), and wing, both with and without leading-edge flap deflection. A multiblock structured grid strategy is employed to decompose the computational flowfield domain around the subject configuration. Steady-state solutions are obtained from an algorithm that solves the compressible Navier-Stokes equations with an upwind-biased, flux-difference splitting approach. The results presented are based on a fully turbulent flow assumption, simulating the high Reynolds number flow conditions that correspond to a recent FI A-18 flight experiment. Good agreements between the computations and the flight test results are obtained for both surface flow patterns as well as surface pressure distributions. Furthermore, a correlation between the computed LEX vortex-core and the flight test results, observed by way of smoke visualization, is also presented.
Multiblock Navier-Stokes Solutions About the F/A-18 Wing-Lex-Fuselage Configuration
9th Applied Aerodynamics Conference ; 1991 ; Baltimore, MD, US
Journal of Aircraft ; 30 , 3
1993-05-01
Miscellaneous
No indication
English
Multiblock Navier-Stokes Solutions About the F-A-18 Wing-LEX-Fuselage Configuration
Online Contents | 1993
|Multiblock Navier-Stokes solver for wing/fuselage transport aircraft
Tema Archive | 2002
|British Library Conference Proceedings | 1991
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