F111 逆噴射ジェットを伴う垂直離着陸型ロケットの着陸時空力特性(F-11 空気力学(1),一般講演)

概要

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For achieving a fully reusable rocket vertical as a future space transportation system, the conceptual designs of vehicle systems are presently being conducted in ISAS/JAXA. In this system design, aerodynamic design considerations are made on a vertical take-off and vertical landing vehicle. One of the considerable issues of a vertical lander is the effect of the interaction between a supersonic nozzle jet and a free-stream when the vehicle is decelerated by the main engine thrust in the landing phase. In order to investigate the influence of such counter-flow interaction in detail, wind tunnel tests were conducted in low speed wind tunnel in ISAS and ISTA/JAXA. The aerodynamic forces and pressure on the base surface were measured by using a scale model of the vehicle. The velocity distribution was measured by a particle image velocimetry (PIV) technique. The aerodynamic characteristics in the vertical landing phase are affected by not only the reduction of the base pressure but also the flow separation around the model side.
日本流体力学会の論文
2004-08-09