Shock-Induced Turbulence and Acoustic Loading on Aerospace Structures
Final rept. 1 Aug 2014-31 Jul 2015
CRANFIELD UNIV (UNITED KINGDOM)
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An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction SWTBLI is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws MUSCL and Weighted Essentially Non-Oscillatory WENO schemes, 2nd to 9th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation ILES and Reynolds Averaged Navier-Stokes RANS computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37 106m. ILES has been performed for the compression ramp case a moderate Reynolds numbers of 38.7 103, based on the boundary layer thickness, and compared to Direct Numerical Simulations DNS.
- Research and Experimental Aircraft
- Numerical Mathematics
- Fluid Mechanics