Then the flow fields of scramjet combustor with fix geometry and isolator are simulated at different inflow Mach number and the influence of direction of injection fuel to flow structure are analyzed.

 
  • 在此基礎上對固定幾何、帶隔離段的雙模態(tài)超燃沖壓發(fā)動(dòng)機在不同飛行馬赫數下的流場(chǎng)進(jìn)行了模擬,最后分析了不同的燃料噴射方向對燃燒室和隔離段流場(chǎng)的影響。
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