縦渦導入型スクラムジェットの飛行実験(テクニカルフォーラム2 超音速燃焼エンジンの搭載・飛行試験)

抄録

We will present the outline of JAXA's flight experiment of the hypermixer scramjet engine planned for 2005. The principal aims of this flight experiment are 1) to clarify if the ground developed technique for supersonic mixing and combustion enhancement using streamwise vortices can work well in the real flight conditions, and 2) to calibrate the experiments of the High Enthalpy Shock Tunnel (HIEST) by the flight data. The scramjet engine consists of two symmetrically arranged engines. One engine is installed with a hypermixer injector to generate six pairs of streamwise vortices, while the other engine has a backstep injector that generates no streamwise vortices. Fuel is gaseous hydrogen sonically injected at 12°. The engine will be launched by small two-stage rocket using HyShot developed by University of Queensland. Engine data will be obtained at supersonic combustion mode throughout the altitude 34〜23 km at the flight Mach number 7.6.