航天飞机在再入段的亚音速空气动力特性的一种有效算法

本文采用吸力比拟原理,结合基本解的数值计算方法,用来计算航天飞机机翼从小迎角到大迎角(a=0°～30°)的亚音速纵向气动特性;而对零升阻力和机身气动特性,则用工程估算方法计算。由于目前的航天飞机,一般为下单翼的复杂外形翼-身组合体,根据文9]的原理,可忽略翼-身干扰对纵向气动特性的影响。 本文导得可以计及涡效应的任意平面形状边条机翼的亚音速气动特性的计算公式,亦可计算尖梢机翼的展向升力分布。公式中所需的位流系数可采用涡格面元法进行数值计算来获得,压缩性效应则通过位流系数来计及。 本文计算了多种机翼和航天飞机的气动特性。与实验数据比较表明,本方法具有方法简便、计算快速和计算结果具有设计精度的优点,是计算航天飞机亚音速气动特性的一种有效方法。可供航天飞机初步设计使用,亦可作为航天飞机气动优化设计系统中的子系统。经过适当推导,本方法可推广应用于亚音速前缘的超音速情况。

An Efficient Calculation Method of Subsonic Aerodynamic Characteristics for a Space Shuttle Orbiter in the Reentry Attitude

The suction analogy principle combined with vortex-lattice method is used in this paper to calculate the subsonic longitudinal aerodynamic characteristics of the wing of a space shuttle orbiter from small angle of attack to high angle of attack with satisfactory results. For the calculation of zero-lift drag and aerodynamic characteristics of the body, an engineering prediction method is adopted.Taking vortex effects into account formulas have been derived to predict subsonic aerodynamic characteristics for arbitrary strake-wing planforms and spanwise lift distribution of strake-wing with pointed tip.Results of the prediction for several kinds of wing and a space shuttle orbiter are compared with the experimental data showing that it is simple, fast and accurate in calculation. This method is valid for predicting the aerodynamic characteristics of a space shuttle orbiter.