计算斜鼻火箭超音速气流的行进算法

V. P. Halynskyi
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摘要

本文提出了一种计算斜鼻火箭超声速流场的行军算法。该算法的一个特点是前翼的超声速流动计算方向与火箭表面主体部分的超声速流动计算方向不一致。因此,首先在柱面坐标系中计算流过机头的流量,流场参数存储在行进截面上。流场参数存储间隔的起始点和结束点是根据弓形激波与某一平面相交的条件确定的,在该平面上指定一个初始流场来计算通过火箭表面主体部分的流量。流场插值分为两个阶段:首先,在初始数据平面与火箭表面主体部分绑定的柱坐标系中,确定子午段弓形激波的径向坐标;从火箭表面点的径向坐标和弓形激波出发,在主体柱面坐标系的子午截面处确定新的计算网格节点坐标。利用主体柱坐标系中指定的新的计算网格坐标,利用两个坐标系相互关联的表达式确定鼻翼柱坐标系中指定的旧坐标。将存储的流场参数在与机头绑定的圆柱坐标系中进行线性插值,计算出具有计算坐标的点处的流动参数。计算得到的流场作为火箭主体部分进行曲计算的初始数据,本文给出了不同鼻翼角值下的倾鼻火箭在超声速流动中的气动特性计算结果。该算法可用于快速计算具有倾斜元件的火箭气动特性。在此过程中,可以使用带有附加块的火箭流计算标准程序,用于在具有偏移原点的倾斜柱坐标系中存储和插值流场,从而允许改变行进方向。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Marching algorithm to calculate supersonic flow past a tilting-nose rocket
This paper presents a marching algorithm for the calculation of supersonic flow past a tilting-nose rocket. A feature of the algorithm is that the marching direction of supersonic flow calculation for the nose does not coincide with that for the main part of the rocket surface. Because of this, at first flow past the nose is calculated in a cylindrical coordinate system, the flow field parameters being stored at marching cross-sections. The start and the end of the parameter storage interval in the flow field are determined from the condition of the intersection of the bow shock wave with a plane in which an initial flow field is to be specified for the calculation of flow past the main part of the rocket surface. The flow field is interpolated in two stages, First, in the cylindrical coordinate system bound to the main part of the rocket surface in the initial data plane, the radial coordinates of the bow shock wave are determined at meridional sections. From the radial coordinates of points on the rocket surface and the bow shock wave, new computational grid node coordinates are determined at meridional sections in the cylindrical coordinate system of the main part. Using the new computational grid coordinates specified in the cylindrical coordinate system of the main part, old coordinates specified in the cylindrical coordinate system of the nose are determined with the use of expressions that relate the two coordinate systems to each other. The flow parameters at a point with the calculated coordinates are calculated using linear interpolation of the stored flow field parameters in the cylindrical coordinate system bound to the nose. The calculated flow field is used as initial data for the marching calculation of the main part of the rocket, The paper presents the results of calculation of the aerodynamic characteristics of a tilting-nose rocket in a supersonic flow at different values of the nose angle. The proposed algorithm may be used in a prompt calculation of the aerodynamic characteristics of rockets with tilting elements. In doing so, use may be made of a standard program of rocket flow calculation with an added block for the storage and interpolation of the flow field in a tilted cylindrical coordinate system with a shifted origin, which allows the marching direction to be changed.
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