Computational Research on Inviscid, Unsteady, Transonic Flow Over Airfoils.
GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF
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The inviscid transonic flow over an NACA 64A410 airfoil oscillating in pitch in a Mach 0.72 stream was calculated with a program based on the unsteady Euler equations. The airfoil oscillates about a mid-chord axis with attitude alpha 1 deg or - 1 deg at reduced frequency k omega CUinfinty 0.2. The effects of two approximations made in the analysis, handling of boundary conditions at the airfoil surface and at the perimeter of the computation field, have been studied. Author
- Fluid Mechanics