Abstract
Aerodynamic configuration of a cone-derived waverider is designed according to the Taylor-Maccoll equation. Flow fields are numerically calculated at an on-design flow condition of the Mach number of 5.5, and the aerodynamic characteristics are estimated. The on-design model is manufactured using a numerical controled machine. In a hypersonic wind tunnel testing at the free stream Mach number 5.5 and the unit Reynolds number of 4.34×106(/m), flow fields are observed with Schlieren photographs and oil flow pattern; also aerodynamic characteristics are measured by a three-component balance. As a comparison, a off-design model with a flat lower surface is made and used for tests at the same flow conditions. The results show that shock wave is well attach to the leading edge of the on-design model at zero angle of attack; streamline on the lower surface is conical and cross flow is not observed. The maximum L/D ratio is found to be about 4.0 at the angle of attack of around -1°, which is higher than that of the off-design model.
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