The results obtained in repeated tests show that this test mechanism can be used to measure the pitching damping derivatives for the vehicle models in the transonic and supersonic wind tunnel.
重复性实验结果表明，该装置可用在跨超音速风洞中测量飞行器模型的俯仰阻尼导数。
Instead of the sonic nozzle, low supersonic nozzles have been utilized to solve the choking problem in transonic wind tunnel testing of high angle-of-attack and high blockage.
本文介绍用低超声速喷管代替声速喷管，解决了大迎角大堵塞度跨声速实验时的风洞壅塞问题。
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