Navier-Stokes, flight, and wind tunnel flow analysis for the F/A-18 aircraft

摘要: Computational analysis of flow over the F/A-18 aircraft is presented along with complementary data from both flight and wind tunnel experiments. The computational results are based on three-dimensional thin-layer Navier-Stokes formulation obtained an accurate surface representation fuselage, leading-edge extension (LEX), wing geometry. However, constraints imposed by either solver and/or complexity associated flow-field grid generation required certain geometrical approximations to be implemented in present numerical model. In particular, such inspired removal empennage blocking (fairing) inlet face. computed for three different free-stream conditions compared test pressure coefficients, tuft flow, off-surface vortical characteristics that included breakdown phenomena. Excellent coefficient correlations, terms magnitude overall trend, forebody throughout range conditions. Reasonable agreement was LEX; general correlation tends improve at higher angles attack. vortex structures qualitatively well results. To evaluate results, a investigation conducted determine effects existing configurational differences between vehicle model aerodynamic characteristics. most cases, made had very little effect