Numerical Simulation for the HOPE-X Ascent Configuration

摘要

HOPE-X (H-I1 Orbiting Plane-Experimental) is being underdeveloped as NAL-NASDA project. In the aerodynamic design the aerodynamic characteristics of the plane has been mainly estimated from wind tunnel test results. On a recent rapid progress of the performance of super-computers and an improvement of highly efficient schemes, CFD has been applied to not only simple flow analysis but also multidisciplinary problems. For example, CFD was used as a multidisciplinary tool for dynamic simulations of the SRB booster separation from H-II and structural analysis for the aeroelastic simulations. At the same time the accuracy of CFD analysis has been improved. CFD has owned the accuracy enough to replace wind tunnel tests for a certain simple problem. Due to the complicated geometry of HOPE-X ascent configuration, shock-shock interactions and shock-boundary layer interactions between boosters and the core booster are supposed to be generated. Therefore CFD analysis for the complicated geometry have to be validated. This paper reports the accuracy of CFD analysis by compared with wind tunnel test results in the aerodynamic design for the HOPE-X ascent configuration.