首页> 美国政府科技报告 >PRESSURE DISTRIBUTIONS ON THREE DIFFERENT CRUCIFORM AFT-TAIL CONTROL SURFACES OF A WINGLESS MISSILE AT MACH 1.60, 2.36, AND 3.70 - Volume II - Clipped Delta Tail
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PRESSURE DISTRIBUTIONS ON THREE DIFFERENT CRUCIFORM AFT-TAIL CONTROL SURFACES OF A WINGLESS MISSILE AT MACH 1.60, 2.36, AND 3.70 - Volume II - Clipped Delta Tail

机译:机械1.60,2.36和3.70上的无翼导弹的三种不同形式的aFT-TaIL控制面的压力分布 - 第二卷 - 三角形截尾

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摘要

The results of pressure distribution tests conducted in the Langley Unitary Flan wind tunnel are presented without analysis. The data were obtained for three sets of cruciform aft-tail control surfaces on a wingless missile model at Mach numbers of 1.60, 2.36, and 3.70 for angles of attack from -4° to 20°, model roll angles from 0° to 90°, and tail deflections of 0° and -15°. The test Reynolds number used was 6.6 x 106 per meter.

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