摘要: Four advanced fighter configurations, which differed in wing planform and airfoil shape, were investigated in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.80, 2.00, and 2.16. Supersonic data were obtained on the... 展开
作者 | Wood, R. M. Miller, D. S. | ||
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原报告号 | N8420486 | 总页数 | 117 |
报告类别/文献类型 | NASA / NTIS科技报告 | ||
关键词 | Aerodynamic characteristics Aircraft configurations Fighter aircraft Supersonic airfoils Wind tunnel tests Wing planforms Angle of attack Directional stability Lateral stability Leading edge sweep Longitudinal stability |