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Investigation of upper-surface-blowing nacelle integration at cruise speeds utilizing powered engine simulators

机译：利用动力发动机模拟器研究巡航速度下的上表面吹气短舱集成

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摘要

Various overwing nacelle designs were investigated on a representative four engine short haul aircraft configuration during a combined analytical and experimental program. Design conditions were M sub o = 0.7 and C sub L = 0.4. All nacelles had D shaped nozzle exits and included a streamline contoured design, a low boattail angle reference configuration, and a high boattail angle powered lift design. Testing was done with the design four engine airplane configuration as well as with only inboard nacelles installed. Turbopowered engine simulators were used to provide realistic representation of nacelle flows. Performance trends are compared for the various nacelle designs. In addition, comparisons are presented between analytical and experimental pressure distributions and between flow through and powered simulator results.
机译：在分析和实验相结合的程序中，对具有代表性的四引擎短途飞机配置进行了各种机舱短舱设计研究。设计条件为M sub o = 0.7和C sub L = 0.4。所有机舱都具有D形喷嘴出口，并包括流线轮廓设计，低船尾角参考配置和高船尾角动力提升设计。测试使用设计的四引擎飞机配置以及仅安装了机舱进行。涡轮动力发动机模拟器用于提供机舱流的真实表示。比较了各种机舱设计的性能趋势。此外，还提供了分析压力分布和实验压力分布之间以及流经和动力模拟器结果之间的比较。

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    Meleason E. T.; Wells O. D.;

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  • 年度 1976
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