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Inverse design and Mach 6 experimental investigation of a pressure controllable bump

机译：压力可控凸块的逆设计和6马赫实验研究

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The low kinetic flow starting from the airframe leading edge is a neglected aspect in designing hypersonic air-breathing flight vehicles. Compared with other boundary layer treating technologies, the bump concept can obtain a good balance of boundary layer removal, external drag control, shock system simplification, and integration design flexibility capabilities. On the basis of conventional conical-flow theory and the new 3D inverse design method, this study proposes a pressure controllable bump concept that can generate the bump configuration inversely by the prescribed pressure distribution. The bump/inlet integration pattern is analyzed, and the basic design methodology is presented. To validate whether the pressure distribution can be used in diverting the boundary layer, experimental study of the bump and numerical simulation are conducted. Results show that the bump has generated identical pressure distribution to the design. The bump can also divert approximately 50% of the boundary layer from the incoming low kinetic flow in Mach 6. Compared with the conventional cone-derived bump in Mach 6, the new bump is 25.8% shorter in height. The flow structure is adjusted nearly parallel to the x-direction, thereby promoting the flow quality of the inlet entrance. Hence, the new inverse design method of pressure distribution expands the applicable Mach range of the hypersonic airframe forebody. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：从机身前缘开始的低动力流​​是设计高超音速呼吸飞行器的一个被忽略的方面。与其他边界层处理技术相比，凹凸概念可以在边界层去除，外部阻力控制，减震系统简化和集成设计灵活性功能之间取得良好的平衡。在常规圆锥流理论和新的3D逆向设计方法的基础上，本研究提出了一种压力可控的凸点概念，该概念可以通过规定的压力分布逆向生成凸点形状。分析了凸块/入口的集成模式，并提出了基本的设计方法。为了验证压力分布是否可用于分流边界层，进行了凸块的实验研究和数值模拟。结果表明，凸块产生的压力分布与设计相同。凸块还可以从6马赫进入的低动力学流中转移大约50％的边界层，与马赫6中传统的圆锥形凸块相比，新凸块的高度短了25.8％。几乎平行于x方向调整流动结构，从而提高了入口的流动质量。因此，新的压力分布逆设计方法扩展了高超音速机身前身的适用马赫范围。 （C）2018 Elsevier Masson SAS。版权所有。

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