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美国政府科技报告
>Investigation of the distribution of lift, drag, and pitching moment between the wing and fuselage of a 1/30-scale semispan model of the bell X-5 airplane at a Mach number of 1.24 by the naca wing-flow method
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Investigation of the distribution of lift, drag, and pitching moment between the wing and fuselage of a 1/30-scale semispan model of the bell X-5 airplane at a Mach number of 1.24 by the naca wing-flow method