Experimental Study of High-Altitude Environment Simulation for Space Launch Vehicles
In this work, a high-altitude environment simulation of space launch vehicle has been examined experimentally. One flow condition was used to replicate Mach 6 flight condition for the Korean Space Launch Vehicle (KSLV-II) at an altitude of 65 km. Flow verification was carried out by measuring stagnation pressure, heat flux, and shock standoff distance. Four different configurations of scaled models were used, respectively, to simulate a particular region of the launch vehicle. The models considered examined the shock wave patterns around the launch vehicle, the aerothermodynamic properties on the forebody flow, the aspects of obtaining shock-free technique, and an interaction between nozzle plume and shear layer emanated from the incoming boundary layer of the model.
This work was supported by the Korea Space Launch Vehicle (KSLV-II) funded by the Ministry of Science, Information and Communications Technology, and Future Planning (MSIP, Korea) as well as the BK21 plus program.
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