Abstract
A numerical investigation of the thermal and acoustic effects in high-speed compressible flows is presented. Two case studies are considered: i) transition to turbulence in supersonic flows over a flat plate, and ii) supersonic shock wave turbulent boundary layer interaction (SWTBLI) over a compression ramp. Implicit Large Eddy Simulations (iLES) are performed using the second and fifth order Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and the ninth order Weighted Essentially Non-Oscillatory (WENO) schemes. The aim of this study is twofold: i) to examine the acoustic and thermal effects associated with transitional and turbulent boundary layers, particularly in the near wall region; ii) to investigate the effects of numerical accuracy on acoustic and thermal loading. The results are compared with theoretical models, Direct Numerical Simulations (DNS) and experiments.
Original language | English |
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Title of host publication | 55th AIAA Aerospace Sciences Meeting |
Place of Publication | Reston, VA |
Number of pages | 14 |
DOIs | |
Publication status | Published - 9 Jan 2017 |
Event | 55th AIAA Aerospace Sciences Meeting - Grapevine, United States Duration: 9 Jan 2017 → 13 Jan 2017 http://scitech.aiaa.org/asm/ |
Conference
Conference | 55th AIAA Aerospace Sciences Meeting |
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Abbreviated title | AIAA SciTech 2017 |
Country | United States |
City | Grapevine |
Period | 9/01/17 → 13/01/17 |
Internet address |
Keywords
- thermal effects
- acoustic effects
- high-speed compressible flows
- supersonic flows
- supersonic shock wave turbulent boundary layer interaction
- implicit large eddy simulations
- boundary layers
- direct numerical simulation
- loading