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本文提出了一种预算超音速/高超音速振动平板翼在平均攻角下的气动稳定性的近似解法,并使用二维平板翼的已知的非定常超音速/高超音速统一的精确解和节条理论的近似解,导出了翼面稳定性导数公式。只要翼面前缘产生的激波为附体激波,则这些公式均能用于任意平面形状的翼面在任意攻角下的计算,其结果在几种不同的特殊情况下均能和现有的其它方法的结果很好地吻合。在牛顿理论范围内,本文给出的德定性导数公式则成为较精确的公式。
In this paper, we propose an approximate solution to the aerodynamic stability of a projected supersonic / hypersonic vibrating plate wing at an average angle of attack using a known unsteady supersonic / hypersonic uniform exact solution and two-dimensional plate wing The approximate solution of the theory is derived and the derivative formula of the stability of the airfoil is derived. As long as the shock generated at the leading edge of the airfoil is an attachment shock, these formulas can be used to calculate the airfoil of any planar shape at any angle of attack, and the result can be compared with the existing one in several different special cases The results of other methods fit well. In Newton’s theory, the formula given by this paper has become a more accurate formula.