Abstract
Shockwave/turbulent boundary layer interactions are studied by comparing direct numerical simulation and experimental data. Two canonical configurations, a 24-degree compression ramp and shock impinging a wall with reflection, are studied. The Mach number for the incoming boundary layer is 2.9. Re θ in the numerical simulation is 2400. Two experimental data sets are used, namely those of Bookey et al1 at the same flow conditions as the DNS and those of Selig3 at Reg of about 70,000. Mean velocity profiles, wall pressure distribution, mass flux turbulence intensity, 2D density correlation and locations of the flow separation and reattachment are compared. In addition, an analysis of the turbulence structure characteristics for the DNS data is given.
Original language | English (US) |
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Pages | 1629-1648 |
Number of pages | 20 |
DOIs | |
State | Published - 2005 |
Event | 43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: Jan 10 2005 → Jan 13 2005 |
Other
Other | 43rd AIAA Aerospace Sciences Meeting and Exhibit |
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Country/Territory | United States |
City | Reno, NV |
Period | 1/10/05 → 1/13/05 |
All Science Journal Classification (ASJC) codes
- General Engineering