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The understanding of projectile wake flows is important in order to improve range, precision and maneuverability. A wind tunnel model is equipped with various fin configurations expected to change the local pressure on the base. The present study analyzes the pressure in the wake of those wind tunnel models. Pressure measurements using pressure sensitive paint (PSP) are conducted at a Mach number of 2. The results of the PSP measurements are compared to numerical simulations using a detached eddy simulation (DES) method
wind-tunnel, Pressure Sensitive Paint, supersonic flow, pressure, wake, base, fins, spin, recirculation, expansion, numerical simulation, DES, paint, experimental
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