airfoils - -15-10-55101520-1.5-1-0.50.511.522.53CL vs....

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Unformatted text preview: -15-10-55101520-1.5-1-0.50.511.522.53CL vs. AlphaColumn BColumn EColumn HColumn KColumn NColumn QColumn BColumn EColumn HColumn KColumn NColumn QColumn BColumn EColumn HColumn KColumn NColumn QColumn BColumn EColumn HColumn KColumn NColumn QColumn BColumn EAlpha (deg)CL-15-10-55101520-0.1-0.08-0.06-0.04-0.020.020.040.060.08CM vs AlphaColumn CColumn FColumn IColumn LColumn OColumn RColumn CColumn FColumn IColumn LColumn OColumn RColumn CColumn FColumn IColumn LColumn OColumn RColumn CColumn FColumn IColumn LColumn OColumn RColumn CAlpha (deg)CMMH45Eppler 325Eppler 326Eppler 327Eppler 328Eppler 329alphaCLCMalphaCLCMalphaCLCMalphaCLCMalphaCLCMalphaCLCM-10-1.12680.009-10-1.27350.068-10-1.17310.043-10-1.07270.019-10-0.9716-0.006-10-0.8759-0.028-9-1.01030.009-9-1.15450.066-9-1.05360.042-9-0.95270.017-9-0.8512-0.007-9-0.755-0.029-8-0.89360.009-8-1.03510.065-8-0.93380.041-8-0.83240.016-8-0.7305-0.008-8-0.6338-0.031-7-0.77660.009-7-0.91550.064-7-0.81380.039-7-0.71190.015-7-0.6096-0.01-7-0.5125-0.032-6-0.65930.008-6-0.79560.062-6-0.69350.038-6-0.59120.013-6-0.4885-0.011-6-0.3911-0.033-5-0.54190.008-5-0.65740.061-5-0.57290.036-5-0.47030.012-5-0.3673-0.013-5-0.2695-0.035-4-0.42430.008-4-0.44410.059-4-0.45230.035-4-0.34930.01-4-0.2459-0.014-4-0.1479-0.037-3-0.30660.007-3-0.43460.058-3-0.33150.033-3-0.22810.009-3-0.1246-0.016-3-0.0262-0.038-2-0.18880.007-2-0.3140.056-2-0.21050.031-2-0.10690.007-2-0.0031-0.018-20.0954-0.04-1-0.07090.006-1-0.19320.054-1-0.08960.03-10.01430.005-10.1183-0.02-10.2171-0.0420.04690.005-0.07250.0520.03140.0280.13550.0030.2397-0.0210.3386-0.04410.16480.00510.04830.0510.15240.02610.25660.00110.361-0.02310.46-0.04620.28260.00420.16910.04820.27330.02420.3777-0.00120.4821-0.02520.5813-0.04830.40030.00330.28980.04630.39410.02230.4986-0.00330.6032-0.02830.7024-0.0540.51790.00240.41040.04440.51480.01940.6194-0.00540.724-0.0340.8233-0.05350.63530.00150.53090.04250.63530.01750.74-0.00750.8446-0.03250.9439-0.05560.75250.00160.65120.0460.75570.01560.8604-0.0160.965-0.03461.0643-0.05770.869570.77130.03770.87580.01370.9805-0.01271.085-0.03771.1843-0.0680.9862-0.00180.89120.03580.99560.0181.1003-0.01481.2047-0.03981.3039-0.06291.1026-0.00291.01080.03291.11520.00891.2198-0.01791.3241-0.04291.4232-0.065101.2187-0.003101.13010.03101.23440.005101.3389-0.019101.443-0.044101.542-0.067111.3344-0.005111.24890.027111.35320.003111.4576-0.022111.5615-0.047111.6603-0.07121.4497-0.006121.36760.025121.4716121.5758-0.025121.6796-0.049121.7781-0.073131.5646-0.007131.48580.022131.5895-0.002131.6936-0.027131.7971-0.052131.8954-0.075141.6789-0.008141.60350.02141.707-0.005141.8108-0.03141.9141-0.055142.0121-0.078151.7928-0.009151.72070.017151.824-0.008151.9275-0.032152.0305-0.057152.1282-0.081Eppler 330Eppler 331Eppler 332Eppler 333Eppler 334...
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This note was uploaded on 01/15/2012 for the course AAE 490 taught by Professor Andrisani during the Fall '09 term at Purdue University-West Lafayette.

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airfoils - -15-10-55101520-1.5-1-0.50.511.522.53CL vs....

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