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Atc4 airshop stage7/4/2023 ![]() angle of attack, and the freestream Mach number and Reynolds number are 0.3 and 1.25 million, respectively. The configuration is pitched-up from zero up to 60 deg. ![]() This multidisciplinary problem is solved using three sets of equations which consists of the unsteady Navier-Stokes equations, the aeroelastic equations, and the grid displacement equations. The computations are carried out on a dynamic multi-block grid structure. The computational model consists of a delta wing-twin tail configuration. The effect of dynamic pitch-up motion of delta wing on twin- tail buffet response is investigated. Effect of Configuration Pitching Motion on Twin Tail Buffet Response
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