XFOIL Version 6.96 Calculated polar for: NACA 63-415 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9210 0.12577 0.12323 -0.0276 1.0000 0.0095 -19.500 -0.9645 0.11353 0.11083 -0.0343 1.0000 0.0095 -19.250 -1.0022 0.10277 0.09991 -0.0402 1.0000 0.0095 -19.000 -1.0363 0.09301 0.09000 -0.0455 1.0000 0.0094 -18.750 -1.0621 0.08489 0.08173 -0.0500 1.0000 0.0095 -18.500 -1.0816 0.07809 0.07480 -0.0537 1.0000 0.0095 -18.250 -1.0979 0.07193 0.06852 -0.0571 1.0000 0.0095 -18.000 -1.1111 0.06645 0.06293 -0.0601 1.0000 0.0096 -17.750 -1.1206 0.06172 0.05809 -0.0625 1.0000 0.0096 -17.500 -1.1270 0.05751 0.05379 -0.0647 1.0000 0.0097 -17.250 -1.1326 0.05360 0.04978 -0.0666 1.0000 0.0098 -17.000 -1.1361 0.05006 0.04615 -0.0682 1.0000 0.0099 -16.750 -1.1374 0.04692 0.04291 -0.0695 1.0000 0.0100 -16.500 -1.1378 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0.4718 0.6293 3.500 0.7494 0.00740 0.00207 -0.0813 0.4582 0.6359 3.750 0.7766 0.00759 0.00220 -0.0813 0.4362 0.6420 4.000 0.8033 0.00782 0.00235 -0.0812 0.4128 0.6484 4.250 0.8298 0.00806 0.00251 -0.0811 0.3876 0.6546 4.500 0.8535 0.00855 0.00279 -0.0806 0.3386 0.6607 4.750 0.8760 0.00914 0.00315 -0.0799 0.2858 0.6677 5.000 0.8999 0.00960 0.00345 -0.0794 0.2498 0.6741 5.250 0.9233 0.01008 0.00379 -0.0789 0.2143 0.6804 5.500 0.9464 0.01058 0.00414 -0.0783 0.1816 0.6875 5.750 0.9689 0.01110 0.00452 -0.0777 0.1488 0.6939 6.000 0.9910 0.01163 0.00491 -0.0770 0.1185 0.7011 6.250 1.0132 0.01213 0.00530 -0.0763 0.0946 0.7079 6.500 1.0360 0.01255 0.00567 -0.0756 0.0777 0.7148 6.750 1.0579 0.01302 0.00607 -0.0749 0.0620 0.7221 7.000 1.0800 0.01346 0.00645 -0.0741 0.0498 0.7285 7.250 1.1020 0.01387 0.00684 -0.0733 0.0415 0.7359 7.750 1.1459 0.01462 0.00760 -0.0718 0.0328 0.7501 8.000 1.1675 0.01498 0.00798 -0.0710 0.0305 0.7575 8.250 1.1887 0.01533 0.00837 -0.0701 0.0287 0.7652 8.500 1.2085 0.01573 0.00879 -0.0690 0.0271 0.7738 8.750 1.2274 0.01611 0.00922 -0.0677 0.0257 0.7824 9.000 1.2441 0.01647 0.00963 -0.0660 0.0246 0.7923 9.250 1.2593 0.01689 0.01010 -0.0641 0.0234 0.8032 9.500 1.2733 0.01738 0.01064 -0.0621 0.0222 0.8147 10.000 1.3022 0.01838 0.01177 -0.0585 0.0205 0.8405 10.250 1.3156 0.01895 0.01240 -0.0568 0.0194 0.8545 10.500 1.3277 0.01959 0.01311 -0.0549 0.0185 0.8709 10.750 1.3384 0.02027 0.01388 -0.0528 0.0177 0.8936 11.000 1.3467 0.02084 0.01459 -0.0502 0.0170 0.9424 11.250 1.3607 0.02161 0.01543 -0.0491 0.0161 1.0000 11.500 1.3731 0.02253 0.01637 -0.0479 0.0152 1.0000 11.750 1.3850 0.02353 0.01739 -0.0467 0.0144 1.0000 12.000 1.3972 0.02453 0.01843 -0.0456 0.0138 1.0000 12.250 1.4086 0.02563 0.01956 -0.0445 0.0131 1.0000 12.500 1.4192 0.02682 0.02079 -0.0434 0.0125 1.0000 12.750 1.4292 0.02810 0.02211 -0.0424 0.0121 1.0000 13.000 1.4385 0.02948 0.02352 -0.0415 0.0117 1.0000 13.250 1.4482 0.03085 0.02495 -0.0406 0.0114 1.0000 13.500 1.4573 0.03233 0.02648 -0.0398 0.0111 1.0000 13.750 1.4657 0.03389 0.02809 -0.0391 0.0109 1.0000 14.000 1.4734 0.03555 0.02982 -0.0384 0.0106 1.0000 14.250 1.4806 0.03731 0.03163 -0.0378 0.0104 1.0000 14.500 1.4873 0.03916 0.03354 -0.0373 0.0102 1.0000 14.750 1.4932 0.04114 0.03556 -0.0368 0.0100 1.0000 15.000 1.4981 0.04327 0.03776 -0.0365 0.0098 1.0000 15.250 1.5022 0.04557 0.04011 -0.0362 0.0096 1.0000 15.500 1.5051 0.04808 0.04268 -0.0361 0.0094 1.0000 15.750 1.5099 0.05043 0.04511 -0.0361 0.0093 1.0000 16.000 1.5141 0.05291 0.04767 -0.0362 0.0092 1.0000 16.250 1.5172 0.05559 0.05043 -0.0364 0.0091 1.0000 16.500 1.5199 0.05840 0.05332 -0.0367 0.0091 1.0000 16.750 1.5220 0.06134 0.05633 -0.0371 0.0089 1.0000 17.000 1.5231 0.06447 0.05955 -0.0377 0.0089 1.0000 17.250 1.5241 0.06771 0.06288 -0.0384 0.0088 1.0000 17.500 1.5244 0.07112 0.06637 -0.0392 0.0087 1.0000 17.750 1.5235 0.07475 0.07009 -0.0402 0.0086 1.0000 18.000 1.5218 0.07858 0.07401 -0.0414 0.0086 1.0000 18.250 1.5196 0.08258 0.07811 -0.0427 0.0085 1.0000 18.500 1.5166 0.08679 0.08241 -0.0442 0.0084 1.0000 18.750 1.5130 0.09115 0.08687 -0.0458 0.0084 1.0000 19.000 1.5085 0.09576 0.09158 -0.0477 0.0083 1.0000 19.250 1.5033 0.10054 0.09646 -0.0497 0.0082 1.0000