NASA NACA-TN-4117-1957 Experimental investigation of lift drag and pitching moment of five annular airfoils《五个环形机翼升力 阻力和俯仰力矩的实验研究》.pdf

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NASA NACA-TN-4117-1957 Experimental investigation of lift drag and pitching moment of five annular airfoils《五个环形机翼升力 阻力和俯仰力矩的实验研究》.pdf_第1页
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NASA NACA-TN-4117-1957 Experimental investigation of lift drag and pitching moment of five annular airfoils《五个环形机翼升力 阻力和俯仰力矩的实验研究》.pdf_第3页
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NASA NACA-TN-4117-1957 Experimental investigation of lift drag and pitching moment of five annular airfoils《五个环形机翼升力 阻力和俯仰力矩的实验研究》.pdf_第4页
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NASA NACA-TN-4117-1957 Experimental investigation of lift drag and pitching moment of five annular airfoils《五个环形机翼升力 阻力和俯仰力矩的实验研究》.pdf_第5页
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1、TECHNICALNOTE4117EXPERIMENTALINVESTIGATIONOF IJI?T, DRAG,ANDPITCHINGMOMENTOF FTVEANNULARAIRFOILSByHermanS. FletcherLangleyAeronauticalLaboratoryLangleyField, Va.WashingtonOctober1957Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARYKAFB,NMF

2、WTIONALADVISORYCO a = 19.5. L-57-2708Figure 13. - Tuft-gridphotographsof flow behind variow wings.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . .-x= 1.5. tx s 25.5(b) A = 2/3; a = 20.1. L-57-2709Figure 13. - Continued.* .Provided by IHSNot for

3、ResaleNo reproduction or networking permitted without license from IHS-,-,-,x. 3.125(c)x = 27. E?5A= 1.0; a = 13.5. L-57-2p.oFigure 13.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-RI.FX = 6.0Ix = 30.0(d) A= 1.5; u= 16.0. Ir57-27KlW3ure 13. - Continued.r a71 ,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I tx . 4.3p3wI ,(e) A= 3.0; a= 12.0. L.5T-2Figure 13. - Concluded.x= 28.x25Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

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