In this paper, an approximate analytical method is developed by which pitching derivatives are predicted for three dimensional wings with pointed leading edge in supersonic and hypersonic stream.
本文给出计算超声速和高超声速尖前缘三维机翼俯仰导数的一个近似解析方法。
The test mechanism for measuring pitching damping derivatives and data reduction equations for obtaining pitching dynamic derivatives have been outlined.
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。
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。
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