境界要素法による超音速非定常流解析用プログラムの開発

抄録

A boundary element method program for unsteady supersonic flow around arbitrary configurations has been developed. The fundamental formulation is based on Morino's method, the application of which to unsteady supersonic flow had been very limited before the present work. Linear distribution of doublet is adopted to ensure the continuity of the strength on panel edges. The exponential terms in the integrands are approximated by using Maclaurin expansion. Flow around oscillating wings is simulated and the results are shown to be consistent with previously known numerical results or with wind tunnel tests. The effects of the angle of attack and the wing thickness, both of which could not be treated by previous methods, are evaluated and it is shown that the effect of the latter is not negligible to assess the unsteady aerodynamic force on wings correctly.