To improve the aerodynamic characteristics of Reusable Launch Vehicles (RLV), active flow control methods with blowing have been investigated. The testing model is lifting body configuration with rounded leading edge and sweepback angle of 70 degrees. For the active flow control, the blowing along the upper surface of lifting body was chosen. The experiments was conducted in transonic wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency). The measurements of aerodynamic forces, flow visualizations and static pressure were conducted. In the series of experiments the increase of lift coefficient at higher angle of attack and the decrease of drag coefficient at lower angle of attack were observed in some conditions of the location of blowing and the sweptback angle and direction of the nozzle for active flow control. As a result the increase of ratio of Lift to Drag is observed among wide range of angle of attack in those selected conditions.
|ジャーナル||Memoirs of the Faculty of Engineering, Kyushu University|
|出版ステータス||出版済み - 12 1 2008|
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