The relevance functions between total pressure recover coefficient and the parameters( Mach number, angle of attack, flow coefficient, angle of sideslip) for subsonic submerged inlet in turbojet and turbofan engine were investigated.

• 摘要根据某埋入式进气道试验数据建立了计算埋入式亚声速进气道总压恢复系数的经验公式，表现为关于马赫数、量系数、角、滑角的函数。