Effect of microramps on flare-induced shock – boundary-layer interaction
| Autor: | A. Misra, G. N. Joshi, T. Nilavarasan |
|---|---|
| Rok vydání: | 2019 |
| Předmět: |
020301 aerospace & aeronautics
Materials science Bubble Rotational symmetry Aerospace Engineering 02 engineering and technology Mechanics Boundary layer thickness 01 natural sciences 010305 fluids & plasmas law.invention Downwash symbols.namesake Flow control (fluid) Boundary layer 0203 mechanical engineering Mach number law 0103 physical sciences symbols Flare |
| Zdroj: | The Aeronautical Journal. 124:121-149 |
| ISSN: | 2059-6464 0001-9240 |
| Popis: | The ability of microramps to control shock - boundary layer interaction at the vicinity of an axisymmetric compression corner was investigated computationally in a Mach 4 flow. A cylinder/flare model with a flare angle of 25° was chosen for this study. Height (h) of the microramp device was 22% of the undisturbed boundary layer thickness (δ) obtained at the compression corner location. A single array of these microramps with an inter-device spacing of 7.5h was placed at three different streamwise locations viz. 5δ, 10δ and 15δ (22.7h, 45.41h and 68.12h in terms of the device height) upstream of the corner and the variations in the flowfield characteristics were observed. These devices modified the separation bubble structure noticeably by producing alternate upwash and downwash regions in the boundary layer. Variations in the separation bubble’s length and height were observed along the spanwise (circumferential) direction due to these devices. |
| Databáze: | OpenAIRE |
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