Numerical Simulation of Effect of Angle of Attack on a Supersonic Parachute System
In the present study, a detailed investigation of unsteady supersonic flows around rigid parachute models is performed by numerically solving three-dimensional compressible Navier-Stokes equations at a freestream Mach number of 1.5. The parachute system employed here consists of a capsule and a canopy. The cases with different capsule angles of attack (α) are simulated. The objective of this study is to examine the effects of capsule angle of attack on the flow fields and investigate ways to suppress the complicated aerodynamic interactions around the parachute models. As a result, it is found that as α is increased, the unsteady pulsation flow mode is weaken, and it almost disappears at α =10 deg.
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