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Evaluation of wave drag reduction by flow control

机译：通过流量控制评估波浪阻力减小

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摘要

An analytical expression is proposed to estimate the wave drag of an aerofoil equipped with shock control. The analysis extends the conventional approach for a single normal shock wave in the absence of control, based on the knowledge that all types of successful shock control on transonic aerofoils cause bifurcated λ-shock structures. The influence of surface curvature on the λ-shock structure has been taken into account. The extended method has been found to produce fairly good agreement with the results obtained by CFD methods while requiring negligible computational effort. This new formulation is expected to be beneficial in the industrial design process of transonic aerofoils and wings where a large number of computational simulations have to be performed.
机译：提出了一种解析表达式来估计装备有冲击控制装置的机翼的波浪阻力。该分析基于对跨音速翼型的所有成功的冲击控制都会引起分叉的λ冲击结构的认识，将传统方法在没有控制的情况下扩展到单个法向冲击波。已经考虑了表面曲率对λ冲击结构的影响。已发现扩展方法与CFD方法获得的结果产生了很好的一致性，而所需的计算工作却可以忽略不计。有望在需要进行大量计算模拟的跨音速翼型和机翼的工业设计过程中受益于这种新配方。

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