基于投影法的双后掠乘波体气动性能

双后掠布局能有效改善乘波体低速时的气动性能不足。为了获得双后掠乘波体，目前常采用的是定前缘型线的吻切锥乘波体设计方法，但该设计方法存在设计过程复杂，激波出口型线与理论不一致等问题。而采用直接投影获得双后掠乘波体的设计方法可以解决上述问题。为了系统研究基于投影法的双后掠乘波体的气动性能，使用CFD方法分析了采用该方法生成的双后掠乘波体在高超声速与低速时的气动性能。结果表明，该方法获得的乘波体在高超声速下的气动性能与定前缘型线的双后掠乘波体相当。且此方法仍保留了高超声速下"波效应"引起大攻角非线性升力、低速下"涡效应"有效提高升阻比等双后掠乘波体的优良气动特征，为基于投影法的双后掠乘波体的工程应用提供了指导。

Aerodynamic performance of double swept waverider based on projection method

The double sweepback layout can effectively improve the aerodynamic performance of the waverider in the subsonic state. At present, the double swept waverider is mainly designed by the osculating-cones method with leading edge-customized. However, there are still some problems in this method, such as complexity of the design process and inconsistency between the actual and the theoretical inlet capture curve. Given that, we take the projection method to design the double swept waverider directly. To systematically research the aerodynamic performance of the double swept waverider obtained by the projection method at the subsonic and hypersonic speeds, the CFD method is applied. Results show that the aerodynamic performance of the double swept waverider designed by the projection method is equivalent to that designed with the leading edge-customized method in the hypersonic state. Moreover, the double swept waverider obtained by the projection method still retains the excellent aerodynamic characteristics of the double-swept waverider, such as the "wave effect" at hypersonic speeds, which causes nonlinear lift at large angles of attack, and the "vortex effect" at low speeds which effectively improves the lift-drag ratio. The results in this paper can provide some guidance for the engineering application of the double swept waverider based on the projection method.