Abstract The planform-customized waverider developed from the osculating-cone method enables the design of a double swept waverider to remedy some deficiencies for the waverider. To analyze the aerodynamic performances, two models of the double swept waveriders, with cusp head and bend head shape, respectively, were fabricated for the wind-tunnel test, and a single swept waverider model was constructed as the compared configuration. A set of experiments at the design Mach number were performed in the hypersonic wind tunnel FD-07 of our institute. Combining computational fluid dynamics (CFD) simulations, the effect of leading-edge bluntness, the aerodynamic forces and longitudinal stability were studied experimentally and numerically. The bluntness of leading-edge area reduced the lift-to-drag ratio (L/D) significantly. The aerodynamic performances obtained from wind-tunnel tests and CFD simulations were very close, marking a difference in L/D of less than 1% in the design state. The data from both wind-tunnel experiments and CFD simulations implied that the double swept waverider maintained “wave-riding” performance in the hypersonic state, and their longitudinal stability improved dramatically compared with the single swept configuration. The results verified the design method of the double swept waverider and its advantages in aerodynamic performance.
Highlights Aerodynamic performances of double swept waveriders were studied experimentally. Leading-edge bluntness reduced lift-to-drag ratio in wind-tunnel tests. Wave-riding performance of double swept waverider was maintained. Longitudinal stability of double swept waverider improved dramatically.
Experimental and numerical investigation for hypersonic performance of double swept waverider
Acta Astronautica ; 200 ; 291-300
2022-08-05
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Double Swept Waverider from Osculating-Cone Method
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