Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
University of Tokyo Graduate School
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
University of Tokyo Graduate School of Engineering
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
Wind tunnel tests were performed to investigate rolling moment characteristics of a cranked arrow wing SST configuration at high incidence angles. Force measurements and surface static pressure measurements were conducted with the model rolled statically. In order to understand behaviors of the leading edge separation vortex, stereoscopic PIV survey was performed at x/C(sub r) = 0.55 and x/C(sub r) = 0.83. With increasing roll angles, linearly stable rolling moments were obtained at low incidence angles, while abrupt changes from stable to unstable rolling moments were obtained at incidence angle of 20 degrees. Abrupt change of the rolling moment was strongly related to sudden increments of nose down pitching moments. Variations of suction peaks on pressure distributions at x/C(sub r) = 0.83 contribute to unstable rolling moment component. These variations of suction peaks that induce unstable rolling moment are related to the vortex breakdown characteristics. The asymmetry of the chordwise locations of the inboard vortex breakdown on windward and leeward wings induces the sudden change of rolling moments. Because of the effects due to retreating of the vortex breakdown on the leeward wing are larger than those due to moving forward of the vortex breakdown location on the windward wing, sudden increment of the nose down pitching moments was obtained.
超音速航空機(SST)形態の低速高迎角ロール特性に関する研究
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