【摘要】 本文给出了非对称再入飞行器的超音速三维无粘流场的数值计算方法。它归结为求解三个自变量—阶定常拟线性双曲型偏微分方程组的初边值问题。采用MacCormack二步显式差分格式。 为了说明计算方法的实际能力,对弯头钝锥和带控制翼的再入体作了计算。其精确度是令人满意的。更多还原

【Abstract】 The paper describes a numerical method for evaluation of the three-dimensional inviscid supersonic flow about the re-entry vehicles of non-symmetrical bodies. The method is devoted to determining the initial-boundary value problem for hyperbolic partial differential equations in the conservation law form. The MacCormack’ s explicit finite-difference schemes with second order accuracy is adopted. For a bent sphere-cones, different oriented cylindrical coordinate systems are used in different cone regions. The computation of the body surface points is different from reference[ 1,2].The numerical examples of the bent sphere-cones and the re-entry vechicles with control flaps have been worked out to demonstrate the capability of this technique. The accuracy of the results has been examined.更多还原