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Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20 Chord Flap

机译：压缩的上期修正的NaCa 65,3-019翼型的压力和力作用在具有0.20和弦皮瓣影响

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Wind-tunnel tests were made through angle of attack range of -2 to +12 degrees at flap deflections from 0 to -12 degrees. Mach range was 0.28 to 0.74. Additional pressure-distribution measurements were made for positive (down) deflections of the flap at angles of attack of 2 and 4 degrees. Results show that effectiveness of the trailing edge type control surface rapidly decreases and approaches zero as the Mach number increases above critical value.

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作者
Lindsey, W. F.;
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年度 1946
页码 1-85
总页数 85
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Flaps(Control surfaces) ; Wind tunnel tests ; Compressive properties ; Leading edges ; Deflection ; Angle of attack ; Mach number;

机译：翼片（控制面）;风洞试验;压缩性能;前缘;挠度;攻角;马赫数;

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Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20 Chord Flap

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