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中文摘要：
针对高超声速内收缩进气道宽马赫数范围工作的要求,设计了一种四段修型弥散反射激波中心体基准流场,可明显提高基准流场来流马赫数高于设计点来流马赫数（6.0）时的压缩效率,巡航点（来流马赫数为7.0）出口总压恢复系数较下凹圆弧中心体基准流场提高了2.3%.此外,基于两种基准流场分别设计了圆形进口内收缩进气道并在来流马赫数为5.0~8.0范围内进行数值计算,结果表明：来流马赫数高于设计点来流马赫数时,四段修型进气道的压缩效率更高.有黏条件下,来流马赫数为8.0时二者的增压比近似相等,四段修型进气道喉道截面出口总压恢复系数相对提高了1.1%.
英文摘要：
A basic flowfield with center body consisting of four spline curves diffusing reflected shock wave was designed to meet the operation requirement of the hypersonic in- ward turning inlet in a wide Mach number range. The compression efficiency increased obvi ously when the incoming flow Mach number was higher than that of the design point （6.0）, and the exit total pressure recovery coefficient increased by 2.3% compared with the basic flowfield with concave arc center body at cruise point （incoming flow Mach number of 7.0）. Besides, the inward turning inlets with circular shape intake were designed based on these two categories of basic flowfield. The numerical simulation results from the incoming flow Mach number of 5.0-8.0 indicate that the four spline curves inlet has higher compression efficiency when the incoming flow Mach number is higher than that of the design point. The pressure ratio is approximately equal while the throat exit total pressure recovery coefficient of four spline curves inlet increases by 1.1% when the incoming flow Mach number of 8.0 under viscous condition.
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