Abstract
The separation maneuver of an idealized two-stage hypersonic vehicle is aerodynamically investigated at a freestream Mach number of 6.8. The focus is on the calculation of unsteady ow elds arising from a pitching and a translatorymotion as part of the complete separationmaneuver. The numerical simulations are based on a nite volumemethod for solutions of the two-dimensional unsteady Euler and Navier–Stokes equations. The method is employed to compute the hypersonic ow over a blunt orbital stage including the recirculation zone in the rear of the orbital vehicle. The carrier stage is modeled as a at plate parallel to the undisturbed ow. The orbital stage, interfering with the carrier, performs a de nedmotion at zero incidence. The results include theMach number and pressure distributions, as well as the aerodynamic coef cients. The separation process is dominated by re ecting shock waves occurring during the maneuver between the carrier stage and the orbital stage. The position and intensity of the shock waves are a function of speed, distance, and incidence between the two stages. The main intention is to analyze the motion-inducedunsteady aerodynamic effects and the associated ow physics predicted by Euler and Navier–Stokes solutions.
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