Numerical Study on the Influence of Suction near Expansion Corner on Separation Bubble
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| Published in: | Aerospace vol. 12, no. 2 (2025), p. 89 |
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MDPI AG
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| Online Access: | Citation/Abstract Full Text + Graphics Full Text - PDF |
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| 035 | |a 3170836783 | ||
| 045 | 2 | |b d20250101 |b d20251231 | |
| 084 | |a 231330 |2 nlm | ||
| 100 | 1 | |a Zhang, Yaowen |u High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China; <email>ywzhang@stu.wzu.edu.cn</email> (Y.Z.); <email>yangdg-cardc@163.com</email> (D.Y.) | |
| 245 | 1 | |a Numerical Study on the Influence of Suction near Expansion Corner on Separation Bubble | |
| 260 | |b MDPI AG |c 2025 | ||
| 513 | |a Journal Article | ||
| 520 | 3 | |a Suction is an important control method in the shock wave and boundary layer interaction (SWBLI). Aimed at the problem of separation bubbles induced at the expansion corners, this study investigates the influence of suction on both the dimensions of bubble and the structure of the flow field at varying positions and back pressures under Ma = 2.73. As the upstream suction hole moves to the shoulder point, the size of the separation bubble decreases slightly. The decrease in back pressure leads to an increase in flow deflection angle αh. The low-kinetic-energy fluid in the boundary layer is removed and the thickness of the boundary layer decreases. Suction downstream of the shoulder point leads to an obvious change in separation bubble size. When the bleed position is upstream of the actual location of incident shock (Ddown = 2δ), the separation zone is located at the trailing edge of the hole, and the convergence of the separation shock wave (SS) and the barrier shock wave (BSW) leads to a large increase in the pressure plateau. At the downstream of the incident shock (Ddown = 5δ), the separation zone is situated at the leading edge of the hole, resulting in a substantial reduction in the size of the separation bubble. The flow reaches 88.5% of the theoretical expansion value at the shoulder point and directly turns into the bleeding area at the leeward side of the separation bubble. The deflection angle αh reaches the maximum of 46°, and the sonic flow coefficient Qsonic increases significantly. At the theoretical incident shock position (Ddown = 7δ), the separation zone is far from the suction hole position; the two are almost decoupled. The size of the bubble increases rapidly and the reattachment shock wave (RS) appears. | |
| 653 | |a Deflection | ||
| 653 | |a Suction | ||
| 653 | |a Vortices | ||
| 653 | |a Flow coefficients | ||
| 653 | |a Boundary layers | ||
| 653 | |a Shock waves | ||
| 653 | |a Separation | ||
| 653 | |a Numerical analysis | ||
| 653 | |a Pressure distribution | ||
| 653 | |a Position (location) | ||
| 653 | |a Bubbles | ||
| 653 | |a Control methods | ||
| 653 | |a Impact strength | ||
| 653 | |a Reynolds number | ||
| 653 | |a Thickness | ||
| 653 | |a Boundary layer interaction | ||
| 653 | |a Upstream | ||
| 653 | |a Efficiency | ||
| 653 | |a Flow deflection | ||
| 700 | 1 | |a Wang, Shaozhan |u School of Mechanical, Electronic and Control Engineering, Beijing Jiaotong University, Beijing 100044, China; <email>23121367@bjtu.edu.cn</email> | |
| 700 | 1 | |a Yang, Dangguo |u High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China; <email>ywzhang@stu.wzu.edu.cn</email> (Y.Z.); <email>yangdg-cardc@163.com</email> (D.Y.) | |
| 700 | 1 | |a Dong, Bin |u High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China; <email>ywzhang@stu.wzu.edu.cn</email> (Y.Z.); <email>yangdg-cardc@163.com</email> (D.Y.) | |
| 773 | 0 | |t Aerospace |g vol. 12, no. 2 (2025), p. 89 | |
| 786 | 0 | |d ProQuest |t Advanced Technologies & Aerospace Database | |
| 856 | 4 | 1 | |3 Citation/Abstract |u https://www.proquest.com/docview/3170836783/abstract/embedded/7BTGNMKEMPT1V9Z2?source=fedsrch |
| 856 | 4 | 0 | |3 Full Text + Graphics |u https://www.proquest.com/docview/3170836783/fulltextwithgraphics/embedded/7BTGNMKEMPT1V9Z2?source=fedsrch |
| 856 | 4 | 0 | |3 Full Text - PDF |u https://www.proquest.com/docview/3170836783/fulltextPDF/embedded/7BTGNMKEMPT1V9Z2?source=fedsrch |