吸气式高超声速飞行器边界层控制研究概述

吸气式高超声速飞行器是近空间飞行器研究的重要内容之一.文章概述了近年来美国NASA兰利研究中心使用Hyper-X模型进行吸气式高超声速飞行器边界层主动和被动控制研究的情况.NASA兰利研究中心在20in马赫数6和31in马赫数10风洞使用Hyper-X模型进行了高超声速边界层控制主动和被动方法研究,评估了强迫转捩几种概念的有效性,包括使用被动离散粗糙元和主动质量增加(吹气).被动粗糙度研究产生的后掠斜坡构型已经成功用于马赫数7飞行试验.介绍了研究采用的各种边界层主、被动控制构型及试验模型热传导分布、激波系分布和表面流谱测量方法;对部分边界层主、被动控制典型结果进行了比较.

The review of boundary layer control for hypersonic air-breathing vehicle

One of the near-space-vehicle researching efforts is to develop air-breathing hypersonic vehicles.Active and passive methods for tripping hypersonic boundary layers in NASA Langley Research Center using a Hyper-X model have been reviewed.Active and passive methods for tripping hypersonic boundary layers have been examined in NASA Langley Researach Center wind tunnels using a Hyper-X model.The investigation assessed several concepts for forcing transition,including passive discrete roughness elements and active mass addition(or blowing),in the 20-inch Mach 6 and the 31-inch Mach 10 tunnels.The swept ramp configuration resulted from the passive roughness study has been used for Mach 7 flight test successfully.Several configurations of active and passive tripping devices and the measuring methods of heat transfer distributions,shock system details and surface streamline patterns on test models have been presented.The comparisons of some typical test results for active and passive boundary layer controls were conducted.