Investigations for Flow Around slender bodies at high angles of attack

本文采用低速风洞流场显示/测力和数值模拟相结合的方法，对细长体大迎角绕流及其气动特性进行了研究，主要结论如下：1.轴对称体绕流在60 ° ~ 75 °攻角范围内表现出非对称性，并产生非对称侧向力.对轴对称体有效的“非线性气动力特性出现在迎角约为物体锥角的两倍处”的经验规律也适用于非轴对称体.当前翼附着在细长体上时，在一定程度上减少了非对称侧向力的发生，证明了应用于航天运输系统侧向控制的可能性.采用Navier-Stokes分析方法可以在一定程度上模拟出绕流的流动结构和气动特性。三维分离流的结构（节点、焦点、鞍等）可以基于Navier-Stokes方程的计算结果来数值地获得。

Investigations for flow around the slender bodies at high angles of attack and the related aerodynamic characteristics are carried out with the use of both the flow visualization/force measurements in the low speed wind tunnel and the numerical simulation.The major conclusions are as follows:1. Flow around the axisymmetric bodies shows the asymmetries at angles of attack of 60-75 deg and it causes the asymmetric side force.2. The empirical law that "the nonlinear aerodynamic characteristics appears at angle of attack as approximately twice as cone angle of body" which is effective to axisymmetric body can be also applied to the non-axisymmetric bodies.3. When the foreplane is attached on the slender body, it somewhat alleviates the occurrence of asymmetric side force and demonstrates the possibility of application to lateral control of space transportation system.4. Flow structure and aerodynamic characteristics can be simulated in some extent with the Navier-Stokes analysis. The structures of the three-dimensional separated flow (nodes, foci, saddles, etc.) can be numerically obtained based on the computational results of Navier-Stokes equations.