The complicated real gas effects occurring at hypersonic speeds influence the vehicle’s performance and design. Therefore, it is important to incorporate high-fidelity techniques, such as computational fluid dynamics (CFD), into the design and optimization process. This work builds a reliable and efficient gradient-based optimization approach that incorporates CFD using analytical sensitivity techniques. A shape optimization approach is developed using Bézier curves and radial basis functions to define the geometry. An intrusive analytical sensitivity analysis is developed to solve the sensitivity equations with a generalized minimum residual solver and leverages the line-implicit solver employed in the CFD to precondition the system. This technique is applied to the geometry of a hypersonic reentry vehicle, IRV-2, to reduce the drag without increasing the pressure, heat flux, or total surface heat transfer rate into the vehicle. This research considers the shape of the entire vehicle and produces a reduction in total vehicle drag of up to 5.7%. The optimization is performed at three IRV-2 trajectory points, individually, to understand the influence of flight conditions on the optimized design. Although the lower altitude optimized designs produce a smaller reduction in drag, they consistently reduce drag when evaluated along the first portion of the trajectory.
Aerothermodynamic Sensitivity Analysis and Optimization of Hypersonic Reentry Vehicle
01.01.2025
Aufsatz (Konferenz) , Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch