Abstract
¶An experimental study on the effects of fuselage configurations for Reusable Launch Vehicle (RLV) on aerodynamic characteristics has been conducted. In the experiments circular, square and triangle cross sections are selected for the fuselage models of RLV. Aerodynamic forces of those models are measured and flow fields around those models are visualized by smoke-wire technique and oil-flow method. In the present study, the fuselage model with triangle cross section shows the highest values of CLmax and (L/D)max.
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