温敏漆技术及其在边界层转捩测量中的应用

摘要

A temperature sensitive paint (TSP) technique is developed for the request of boundary layer transition measurement,and a test of hypersonic boundary layer measurement of a flat plate is done in CARDC 0.6m shock tunnel.By use of the TSP technique,the measurement of the hypersonic boundary layer transition of slab has been done in the shock tunnel.The test nominal Mach numbers are 8 and 10,the unit Reynolds numbers are 2.45 × 107/m and 4.48 ×106/m respectively,and the yaw angle is 20°.The data of heat transfer and transition position obtained by the TSP and measurement results of the thin film heat transfer sensor match well.The results illustrate that the TSP technique has the ability to measure the hypersonic boundary layer transition of simple model qualitatively and quantitatively in shock tunnel.%边界层转捩测量的需求发展了激波风洞温敏漆技术,并在中国空气动力研究与发展中心(CARDC)0.6m激波风洞上,开展了平板模型高超声速边界层转捩试验测量.试验来流名义马赫数分别为8、10,单位雷诺数分别为2.45×107、4.48×106/m,模型偏航角为20..温敏漆技术测量结果与薄膜热流传感器测量结果在边界层转捩位置及热流大小方面吻合较好.试验结果表明温敏漆技术具备简单模型激波风洞高超声速边界层转捩定性、定量测量试验能力.