Numerical Study on Heat Reduction over Blunt Body withAerodisk/Aerospike

compressible. axisymmetric and full 3D Navier-Stokes equations are solved for a flow over a forward facing spike attached to a heat shield for a free stream Mach number of5. 75 at various angles of attack A numerical simulation is carried out using a finite-volume discretization technique in conjunction with a multistage Runge-Kutta time-stepping scheme. A good agreement is found between them. In numerical analysis, 3-D full Navier-Stokes equations are solved with k-m (SST) turbulence model. The interaction between the shear layer on the spike and the conical-reattachment shock wave causes the peak 0011 pressure and heat flux on the heat shield. The results indicate around 55% reduction in drag for the blunt cone with flat disk at zero degree angle of attack for a free stream Mach number of 5.75. Therefore Surface convective heat-transfer rate measurements have been carried out on the blunt cone with a flat-disk tipped spike of varying length in order to locate the shock reattachment point on the blunt-cone surface. The measured heat-transfer rates fluctuate by about 20o/oin the separated flow region as ~ll as near the reattachment point indicating the unsteady flow field around the spiked blunt cone. The visualized shock structure and the measured Heat on the blunt cone with aerodisk agree well with the numerical simulations. Keywords: Heat Reduction, Aerospike, Numerical Analysis, Hypersonic Flow

کلیدواژه ها:

Heat Reduction ، Aerospike ، Numerical Analysis ، Hypersonic Flow