超音速轴对称头部进气道的内、外流场及外壳压阻计算

为了计算超音速轴对称头部进气道的流场,采用有限差分法编制了一个通用计算程序。该程序适用于皮托式、单锥、双锥、三锥、等熵锥等各种进气道的正问题气动设计。由于在进气道无粘流场计算中,采用了分离奇性的差分方法及混合使用显、隐差分格式,所以在边界点和内点及奇点邻域,计算结果均达到二级精度。程序可瑜出所需要的进气道各内流特性及外流特性。 文中列生了五个计算实例,并与特征线法计算结果和实验结果作了比较。符合程度令人满意。

CALCULATION OF INTERNAL AND EXTERNAL FLOW FIELD AND COWL PRESSURE DRAG IN THE SUPERSONIC AXISYMMETRIC NOSE INLETS

A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary points and internal points, as well as near singular points. This program can offer required internal and external flow characteristics of inlets.Numerical results for five examples are in satisfactory agreement with corresponding results obtained from the method of characteristics and experimental data.