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为估算高超声速类乘波体飞行器的纵向气动力,以三角形面元逼近飞行器外形,根据飞行器迎/背风面情况分别采用达黑姆-巴克法、普朗特-迈耶耳法、切锥法和膨胀波方法计算无粘气动力;通过经验公式估算粘性阻力,并考虑飞行器主要部件之间的气动干扰情况,计算了翼片之间、翼身之间的气动干扰因子,得到整个飞行器的气动力。为验证该方法,以某飞行器为例进行了计算,计算结果与CFD吻合。
In order to estimate the longitudinal aerodynamic force of hypersonic vehicles, the aircraft shape is approximated by triangle bouncing plane. According to the situation of aircraft leeward / leeward, the methods of Darm-Barker, Prandtl-Meier, And the expansion wave method to calculate the non-sticking force. The viscous resistance is estimated by the empirical formula and the aerodynamic interference between the wings and the wing body is calculated taking into account the aerodynamic interference between the main components of the aircraft. The gas of the whole aircraft is obtained power. In order to validate this method, an aircraft was taken as an example and the calculation result was consistent with CFD.