This work uses an immersed-boundary method to simulate the effects of arrays of discrete bleed holes in controlling shock-wave/turbulent-boundary- layer interactions. Both Reynolds-averaged Navier-Stokes and hybrid large-eddy/Reynolds-averaged Navier-Stokes turbulence closures are used with the immersed-boundary technique. The approach is validated by conducting simulations of Mach 2.5 flow over a perforated plate containing 18 individual bleed holes. Computed values of discharge coefficient as a function of bleed plenum pressure are compared to experimental data. Simulations of an impinging-oblique-shock/boundary-layer interaction at Mach 2.45 with and without bleed control are also performed. For the studies with bleed, two different bleed rates are employed. The 68 hole bleed plate is rendered as an immersed object in the computational domain. Wall pressure predictions show that, in general, the large-eddy/Reynolds-averaged Navier-Stokes technique underestimates the upstream extent of axial separation that occurs in the absence of bleed. Good agreement with pitot pressure surveys throughout the interaction region is obtained, however. Flow control at the maximum-bleed rate completely removes the separation region and induces local disturbances in the wall pressure distributions that are associated with the expansion of the boundary-layer fluid into the bleed port and its subsequent recompression. Computed pitot pressure distributions are in good agreement with experiment for the cases with bleed. Swirl-strength probability density distributions are used to estimate the evolution of turbulent length scales throughout the interaction. These, along with Reynolds-stress predictions, indicate that an effect of strong bleed rates is to accelerate the recovery of the boundary layer toward a new equilibrium state downstream of the interaction region.
Bibliographical noteFunding Information:
This work is supported by the U.S. Air Force Office of Scientific Research under grant FA9550-07-1-0191, monitored by John Schmisseur. Computer resources have been provided by the High Performance Computing component of North Carolina State University’s Information Technologies Division. The authors acknowledge John Slater and Mary Jo Long-Davis of NASA John H. Glenn Research Center at Lewis Field for providing digitized experimental data.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science