高超声速风洞试验模型底压测量方法研究

针对高超声速风洞试验模型底压测量误差较大而导致模型底阻难以精确扣除的问题，在Φ1m高超声速风洞中开展了3种底压测量方法的对比研究，即电子扫描压力测量方法、低压力差压传感器测量方法和微型绝压传感器测量方法，并在马赫数6试验条件下开展了HB-2标模和某导弹模型试验验证。试验结果表明:采用微型绝压传感器进行模型底部压力测量能避免测压管路的影响，可快速响应高超声速风洞试验模型底部压力变化情况，有效提高模型底压的测量精准度。

Study on model base pressure measuring technique in hypersonic wind tunnel

It is an experimental technique problem to exactly achieve test model base pressure in hypersonic wind tunnel. Because of the large error of model base pressure measurement before, it is difficult to exactly deduct the model base drag. Three base pressure measuring methods are developed in Φ1m hypersonic wind tunnel, viz. the absolute pressure micro-sensor measuring method, the low pressure differential pressure sensor measuring method and the electronic scanning pressure (ESP) measuring method. The validation tests of HB-2 standard model and a certain missile model are separately conducted at Ma=6. The test results indicate that: the absolute pressure micro-sensor measuring method can avoid the influence of piezometric pipe; it also can rapidly respond the variation of model base pressure with high accuracy.