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本文提出了一种计算超音速非定常气动力的新方法,它将超音速非定常的活塞理论和定常的锥形流理论结合起来,使得被活塞理论所忽略的翼面上各点间的相互影响用锥形流理论来近似计入。文中运用该方法对十个不同平面形状的机翼进行了二十九种状态的颤振计算,并和风洞颤振实验结果作了比较。比较的结果是令人满意的。特别是和用活塞理论所做的颤振分析相比,计算精度有了明显提高。这表明本方法用于超音速颤振分析是确实可行的,它具有方法简洁,计算精度高,计算时间少,程序编制容易的优点。
In this paper, a new method of calculating supersonic unsteady aerodynamics is proposed, which combines the unsteady supersonic piston theory with the constant cone flow theory so that each point on the airfoil neglected by the piston theory The effect is approximated by the cone flow theory. In this paper, the flutter calculation of twenty-nine states on ten different planes of planar wing is made and compared with the experimental results of wind tunnel flutter. The result of the comparison is satisfactory. Especially compared with the flutter analysis made by piston theory, the computational accuracy has been greatly improved. This shows that the method is feasible for supersonic chatter analysis. It has the advantages of concise method, high precision, less calculation time and easy programming.