Assessment of the capability of drag reduction of the shock control device 'SC bump' on airfoil flows and application aspects on wings

机译：评估防震装置“SC凸块”在翼型上的减少的能力和翅膀上的应用方面

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Based on studies abput various concepts to control the shock boundary layer interference the adaptive SC bump seems to be the most efficient shock control device to reduce drag in the off-design condition.The influence of the bump geometry on the drag behaviour is numerically investigated using a DA laminar airfoil and verified by airfoil experiments in the ONERA wind tunnel Ta.In spites of encouraging experimental results in drag reduction with a wing-body configuration equipped with a fixed bump in 3D flow condition,the practical application on wings is not solved due to design and integration problems.

机译：基于研究的各种概念来控制冲击边界层干扰，自适应SC凹凸似乎是最有效的冲击控制装置，以减少缺陷设计条件的拖动。使用数值研究了凸块几何对拖曳行为的影响通过翼型的翼型翼型在OneA风洞Ta中验证了DA层流翼型。在令人鼓舞的实验结果中，在翼身构型中造成翼形的实验结果，用3D流量条件的固定凹凸的翼形配置，翅膀的实际应用尚未解决设计和集成问题。

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《IUTAM symposium on mechanics of passive and active flow control》|1999年||共6页
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G.Dargel; A.M.Rodde; J.P.Archambaud;
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中图分类流体力学;
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1. Quantitative comparison of 2D and 3D shock control bumps for drag reduction on transonic wings [J] . Deng Feng, Qin Ning Proceedings of the Institution of Mechanical Engineers . 2019,第7期

机译：用于减少跨音速机翼阻力的2D和3D防震凸块的定量比较
2. Quantitative comparison of 2D and 3D shock control bumps for drag reduction on transonic wings [J] . Deng Feng, Qin Ning Proceedings of the Institution of Mechanical Engineers . 2019,第7期

机译：2D和3D冲击控制凸起减少跨音翼减阻的定量比较
3. Optimization and analysis of shock wave/boundary layer interaction for drag reduction by Shock Control Bump [J] . Mazaheri K., Kiani K. C., Nejati A., Aerospace science and technology . 2015,第apraamay期

机译：冲击波与边界层相互作用的优化与分析
4. Assessment of the capability of drag reduction of the shock control device "SC bump" on airfoil flows and application aspects on wings [C] . G.Dargel, A.M.Rodde, J.P.Archambaud IUTAM symposium on mechanics of passive and active flow control . 1999

机译：评估防震装置“SC凸块”在翼型上的减少的能力和翅膀上的应用方面
5. The immersed boundary projection method and its application to simulation and control of flows around low-aspect-ratio wings. [D] . Taira, Kunihiko. 2008

机译：浸入式边界投影方法及其在低纵横比机翼周围流动模拟与控制中的应用。
6. Surface drag reduction and flow separation control in pelagic vertebrates with implications for interpreting scale morphologies in fossil taxa [O] . Colin Palmer, Mark T. Young 2015

机译：远洋脊椎动物的表面减阻和水流分离控制对解释化石分类中的鳞片形态具有启示意义
7. Erratum to: The application of the gradient-based adjoint multi-point optimization of single and double shock control bumps for transonic airfoils [O] . K. Mazaheri, A. Nejati, K. Chaharlang Kiani, 2016

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8. Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method [R] . Hammond, Alexander D 1950

机译：四翼弦线后掠60度，纵横比2，锥度比0.6和NaCa 65a006翼型截面的机翼上的襟翼式和扰流式控制器的横向控制研究：跨音速碰撞法

Assessment of the capability of drag reduction of the shock control device 'SC bump' on airfoil flows and application aspects on wings

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