Abstract
A field panel method, FTRAN2, is presented for the calculation of twodimensional inviscid transonic flow including shock waves about an oscillating wing. For a NACA 6UAOO6 and a NACA 6UA010 airfoil results are presented and compared with results of finite difference methods. The good agreement obtained and the lower computer cost shows the feasibility of the method. Also a modification of FTRAN2 is proposed to achieve further reduction of the computational effort. Results are given for an oscillating flat plate as a first test case.
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