The influence of forward flight on the far-field noise of an underexpanded heated supersonic jet has been studied experimentally with a 12.5-cm-diam convergent nozzle operated in the NASA Ames Research Center 12.2x24.4 m (40x80 ft) wind tunnel. The nozzle was operated at pressure ratios up to 4.5 and stagnation temperature rtios from 2.45 to 3.45. The resulting velocity (based on fully expanded condition) range is from 586 to 858 m/s. The freestream Mach number was varied from 0 to 0.32.
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机译：通过在美国国家航空航天局艾姆斯研究中心12.2x24.4 m（40x80 ft）风洞中运行的直径为12.5 cm的会聚喷嘴，实验研究了前向飞行对超膨胀超音速喷气发动机远场噪声的影响。喷嘴在高达4.5的压力比下以及从2.45至3.45的停滞温度rtios下运行。最终速度（基于完全扩展的条件）范围为586至858 m / s。自由流马赫数从0变化到0.32。
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