Numerical research on the unsteady aerodynamics about the delta wing oscillating in pitching at high angle of attack

Numerical simulations are presented about the unsteady flows around the delta wing which oscillate in pitching with large amplitude at high angle of attack. On the basis of the inviscid flow method, the unsteady Euler equations are solved with the explicit finite volume scheme; meanwhile, the implicit residual smoothing with the variable local parameter is implemented; so the computer time CPU can be reduced by a factor of 10 while keeping the second order accuracy of the numerical scheme. The results show that: (1) for the wing oscillating in pitching in the flow, the breakdown of the leeward side vortex is delayed to a higher angle of attack; (2) as the angle of attack changes, the strength of the vortex varies, but the position of the vortex almost does not change; (3) the unsteady lift and moment rings are influenced not only by the angle of attack but also by the oscillating frequency.