Abstract
A numerical computation has been carried out to investigate 3-D shock wave/turbulent boundary layer interactions generated by the sharp fin and the swept compression comer. The upstream flow is at Mach number 3 and Reynolds number 1.06×106 based on the upstream boundary-layer thickness. Reynolds averaged compressible Navier-Stokes equations were solved with turbulence represented by an algebraic eddy viscosity model. The two geometries investigated were 3-D sharp fin with fin angle α = 17.5 deg (17.5 deg fin) and the swept compression comer at an angle of attack λ = 30 deg and with a sweep angle of 60 deg ((30, 60) comer). The two models were selected because of their similar shock strength and shape. Overall, good agreement has been achieved between computation and experiment. Both interaction flowfields were dominated by a large vortical structure aligned with the corner. Computation tends to support the quasiconical free similarity principle proposed previously from experiments. More refined grid resolution is necessary for definite conclusion.
| Original language | English (US) |
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| State | Published - 1989 |
| Event | AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989 - Buffalo, United States Duration: Jun 12 1989 → Jun 14 1989 |
Other
| Other | AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989 |
|---|---|
| Country/Territory | United States |
| City | Buffalo |
| Period | 6/12/89 → 6/14/89 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Condensed Matter Physics
- Electrical and Electronic Engineering
- Engineering (miscellaneous)