Numerical investigation of sideslip angle effects on swept-forward fin shock interactions

Abstract

The influence of sideslip angle on the 3-D asymmetry swept-forward fin shock interactions are analyzed by numerical simulation under Mach number 6.36, Reynolds number 3.27 × 10⁷/m and wedge compression angle 12°. Firstly, the effect of different swept-forward angles on the flow field structure and aerodynamic thermal characteristics under 0° sideslip is analyzed. With the increase of the swept-forward angle, there are three kinds of shock wave interaction in turn on the symmetry plane: type IV interaction, the combination of type II and type III interaction, and type I interaction. Then, a typical swept-forward angle is selected for each interaction type, and the flow characteristics at 10° and 20° sideslip angles are simulated. The results indicate that: Under the influence of the sideslip, the heat distribution on the fin becomes asymmetric, and the maximum heat flux position at the fin’s leading edge shifts from the symmetry plane to the windward side. The sideslip angle affects the maximum heat flux with changes within 10%. At all swept-forward angles, the windward heat flux increases significantly on the sidewall near the fin’s leading edge as the sideslip angle increases. At a 20° sideslip angle, for swept-forward angles of 20° and 30°, the maximum heat flux on the sidewall near the fin’s leading edge exceeds the heat flux at the stagnation point of the two-dimensional cylinder with the same radius under free flow. For swept-forward angles of 45°, the maximum heat flux on the sidewall near the leading edge is 0.74 times that of the two-dimensional cylindrical stagnation heat flux of the same radius under free flow.

Keywords

Shock wave interactions hypersonic aerodynamic heat Computational Fluid Dynamics 3-D shock wave interactions

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