Provision of flight safety during hypersonic flight is a challenging scientific and technical problem. Waverider concept is based on matching the wing leading edge of the shock formed off the vehicle forebody. A hypersonic vehicle spends the major part of its cruise flight in high temperature flow. Design and optimization of waverider at hypersonic speeds is a challenging problem because a large number of variants are required to be computed to achieve a larger lift-to-drag ratios. Numerical simulation of the flowfield around a hypersonic waverider is performed using a high-temperature air model and a hybrid architecture based on graphics processing units. The mathematical model and computational algorithm are verified and validated against CFD benchmark problems. The results obtained show flowfield around hypersonic waverider and its aerodynamic quality at different angles of attack. The scalability of the developed model is investigated, and the results of the study of the efficiency of calculating hypersonic fluidflows on graphics processors are presented. The computational times achieved with the perfect and real gas models are compared.

在高超音速飞行期间提供飞行安全是一个具有挑战性的科学和技术问题。Waverider 概念基于匹配从车辆前体形成的冲击的机翼前缘。高超音速飞行器在其巡航飞行的大部分时间里都处于高温气流中。高超音速下的乘波器的设计和优化是一个具有挑战性的问题，因为需要计算大量变体才能实现更大的升阻比。使用高温空气模型和基于图形处理单元的混合架构对高超声速乘波器周围的流场进行数值模拟。数学模型和计算算法针对 CFD 基准问题进行了验证和验证。获得的结果显示了高超声速乘波器周围的流场及其在不同攻角下的气动质量。研究了所开发模型的可扩展性，并给出了在图形处理器上计算高超声速流体流动的效率的研究结果。比较了完美和真实气体模型的计算时间。