摘要
本文介绍用壁压信息法对高速风洞模型试验进行洞壁干扰修正的方法。这种方法使用风洞壁附近壁压分布测量数据和模型受力数据进行洞壁干扰修正计算,不涉及风洞壁的通气特性,可用于各种通气壁或实壁高速风洞。用本法计算了各种模型在多种风洞试验段(实壁、柔壁、孔壁、缝壁)中的数百种试验状态。试验马赫数范围是0.5到0.9,试验雷诺数范围是2×10~6～1×10~7。计算结果和国外最新修正方法及无洞壁干扰N-S方程计算结果进行了比较,证实了本文方法的正确性和实用性。
Wall-signature methods for wall interference correction in high speed wind tunnel model tests is presented. The methods correct wall interference effects using the measured pressure distribution data near tunnel walls and the model force data. Without the knowl-edge of wall cross-flow properties,they can be used for various ventilated wall or solid wall wind tunnels. Hundreds of test cases including several models in various different tunnels (solid wall,streamline wall perforated wall,slotted wall) are corrected by these methods. The test Mach number range is 0.5 to 0.9. The Reynolds number range is 2×106 to 1×107. The corrected results are compared with the foreign newest corrections and Navier-Stokes free-air solutions. The correctness and practicality of these methods are verified.
关键词
风洞试验
洞壁干扰
跨音速流动
wind tunnel test,wall interference,transonic flow,relativity between wind tun-nel and flight
