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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。
In order to calculate the flow field of the supersonic axisymmetric head inlets, a generalized calculation program was developed by finite difference method. The program is suitable for Pitts type, single cone, double cone, three cone, such as entropy cone and other air intake is positive problem aerodynamic design. Because of the singularity difference method and mixed use of explicit and implicit difference schemes in the calculation of no-viscous flow field in the inlet, the calculation results reach the second-order precision in the boundary point, the inner point and the singular point neighborhood. Procedures can be out of the required inlet of each flow characteristics and outflow characteristics. In the paper, five examples are given and compared with the results calculated by the characteristic line method and the experimental results. Conformity is satisfactory.