VISCOUS-FLOW SIMULATION OF A FIGHTER AIRCRAFT

A computer code capable of solving the three-dimensional compressible, unsteady, Navier-Stokes equations has been developed. This solver has been applied to steady and unsteady subsonic flow past highly swept wings and wing-body-inlet combinations at high angles of attack. Calculations for isolated wings show the formation of a leading-edge vortex. At sufficiently high angles of attack, the lift distribution over the wing begins to oscillate in time. Calculations for wings subjected to a ramp motion reveal substantially higher lift loads prior to stall than for the static fixed angle-of-attack conditions. The results for wing-body-inlet combinations show separated flow off the sharp inlet leading edge, vortex formation over wing-inlet interface region, and over the wing leading edge. The vortex core trajectory and the flowfield agree well qualitatively with the experimental results. The analysis shows near-periodic fluctuations in the sectional lift coefficients with time. A Fourier analysis of the sectional lift coefficients reveals the flowfield to be rich in discrete frequencies. Calculations have also been carried out for a vertical tail configuration, which indicates large lateral forces on the vertical tail due to interaction between the vertical tail and the vortical flow off the wing-body-inlet configuration.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
1992
Language
ENG
Citation

JOURNAL OF AIRCRAFT, v.29, no.5, pp.886 - 891

ISSN
0021-8669
DOI
10.2514/3.46258
URI
http://hdl.handle.net/10203/10404
Appears in Collection
AE-Journal Papers(저널논문)
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