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本文叙述了测量俯仰阻尼导数的试验装置及其数据处理方程。在FL-23风洞中,测量了AGARD-C模型俯仰阻尼导数,结果表明:阻尼导数随M数的变化趋势是合理的,M=2.5 C模型在FL-23的测量结果同在AEDC 4英尺风洞所得的数据有很好的一致性。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。
This paper describes the experimental device for measuring pitch damping derivative and its data processing equations. In the FL-23 wind tunnel, the derivative of the pitch-damping of the AGARD-C model was measured and the results show that the trend of the damping derivative with the M-number is reasonable. The measurement of the M-2.5C model in the FL-23 is the same as that of the 4-foot AEDC The data obtained from the wind tunnel are in good agreement. Repetitive experimental results show that the device can be used to measure the pitch-dependent damping derivative of the aircraft model in supersonic wind tunnels.