XFOIL Version 6.96 Calculated polar for: NACA 66(4)-221 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.7343 0.09525 0.09169 -0.1038 0.9457 0.0245 -19.250 -0.7638 0.08632 0.08244 -0.1099 0.9359 0.0243 -19.000 -0.7832 0.08028 0.07614 -0.1132 0.9247 0.0242 -18.500 -0.8168 0.07091 0.06631 -0.1158 0.9056 0.0242 -18.000 -0.8376 0.06409 0.05910 -0.1161 0.8908 0.0241 -17.750 -0.8491 0.06045 0.05525 -0.1159 0.8847 0.0242 -17.500 -0.8557 0.05721 0.05180 -0.1155 0.8793 0.0242 -17.250 -0.8582 0.05490 0.04935 -0.1149 0.8738 0.0242 -17.000 -0.8540 0.05227 0.04655 -0.1146 0.8691 0.0244 -16.750 -0.8462 0.05032 0.04448 -0.1143 0.8646 0.0246 -16.500 -0.8378 0.04877 0.04286 -0.1140 0.8601 0.0249 -16.250 -0.8303 0.04701 0.04099 -0.1135 0.8559 0.0249 -16.000 -0.8225 0.04562 0.03953 -0.1130 0.8516 0.0253 -15.750 -0.8120 0.04432 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0.7589 3.250 0.4538 0.01612 0.01142 -0.0299 0.7186 0.7595 3.500 0.4944 0.01564 0.01094 -0.0324 0.7174 0.7600 3.750 0.5329 0.01526 0.01057 -0.0346 0.7160 0.7605 4.000 0.5718 0.01501 0.01032 -0.0369 0.7144 0.7611 4.250 0.5726 0.01522 0.01063 -0.0323 0.7085 0.7621 4.500 0.6048 0.01481 0.01025 -0.0332 0.7048 0.7628 4.750 0.6503 0.01402 0.00944 -0.0364 0.7013 0.7633 5.000 0.7028 0.01323 0.00860 -0.0409 0.6972 0.7637 5.250 0.7117 0.01308 0.00854 -0.0374 0.6896 0.7650 5.500 0.7544 0.01221 0.00760 -0.0400 0.6806 0.7657 5.750 0.7625 0.01202 0.00750 -0.0363 0.6711 0.7669 6.000 0.7908 0.01165 0.00711 -0.0364 0.6626 0.7678 6.250 0.7883 0.01163 0.00718 -0.0307 0.6531 0.7692 6.500 0.7920 0.01154 0.00712 -0.0262 0.6419 0.7706 6.750 0.7904 0.01176 0.00736 -0.0211 0.6259 0.7721 7.000 0.7891 0.01205 0.00758 -0.0161 0.5934 0.7737 7.250 0.7770 0.01276 0.00797 -0.0095 0.5436 0.7752 7.500 0.7617 0.01391 0.00887 -0.0029 0.5022 0.7766 7.750 0.7459 0.01523 0.00997 0.0034 0.4610 0.7781 8.000 0.7349 0.01649 0.01106 0.0086 0.4233 0.7799 8.250 0.7239 0.01790 0.01228 0.0136 0.3820 0.7815 8.500 0.7168 0.01929 0.01348 0.0178 0.3424 0.7831 8.750 0.7119 0.02069 0.01468 0.0216 0.3007 0.7847 9.000 0.7105 0.02200 0.01577 0.0248 0.2574 0.7864 9.250 0.7094 0.02337 0.01690 0.0278 0.2124 0.7881 9.500 0.7089 0.02476 0.01800 0.0306 0.1621 0.7901 9.750 0.7093 0.02618 0.01913 0.0331 0.1140 0.7919 10.000 0.7125 0.02751 0.02021 0.0353 0.0772 0.7936 10.250 0.7203 0.02864 0.02120 0.0369 0.0560 0.7951 10.500 0.7312 0.02965 0.02213 0.0381 0.0472 0.7965 10.750 0.7439 0.03051 0.02299 0.0391 0.0427 0.7984 11.000 0.7556 0.03145 0.02396 0.0403 0.0391 0.8003 11.250 0.7685 0.03235 0.02489 0.0412 0.0367 0.8022 11.500 0.7787 0.03346 0.02602 0.0424 0.0342 0.8041 11.750 0.7917 0.03442 0.02702 0.0432 0.0323 0.8062 12.000 0.8000 0.03571 0.02832 0.0444 0.0308 0.8083 12.250 0.8121 0.03679 0.02945 0.0452 0.0300 0.8105 12.500 0.8247 0.03784 0.03054 0.0459 0.0285 0.8128 12.750 0.8360 0.03901 0.03173 0.0466 0.0277 0.8149 13.000 0.8408 0.04066 0.03338 0.0478 0.0265 0.8171 13.250 0.8523 0.04181 0.03463 0.0485 0.0258 0.8197 13.500 0.8631 0.04305 0.03594 0.0492 0.0255 0.8223 13.750 0.8741 0.04430 0.03725 0.0498 0.0250 0.8250 14.000 0.8846 0.04564 0.03864 0.0504 0.0241 0.8278 14.250 0.8943 0.04706 0.04009 0.0510 0.0235 0.8308 14.500 0.9043 0.04850 0.04155 0.0514 0.0233 0.8335 14.750 0.9128 0.05001 0.04309 0.0521 0.0229 0.8365 15.000 0.9230 0.05140 0.04455 0.0526 0.0225 0.8396 15.250 0.9338 0.05280 0.04606 0.0530 0.0222 0.8430 15.500 0.9452 0.05417 0.04751 0.0533 0.0220 0.8467 15.750 0.9566 0.05558 0.04899 0.0536 0.0216 0.8504 16.000 0.9678 0.05702 0.05050 0.0538 0.0214 0.8542 16.250 0.9784 0.05845 0.05204 0.0541 0.0212 0.8584 16.500 0.9878 0.06004 0.05371 0.0544 0.0207 0.8628 16.750 0.9989 0.06155 0.05529 0.0545 0.0206 0.8674 17.000 1.0104 0.06301 0.05684 0.0546 0.0206 0.8719 17.250 1.0192 0.06468 0.05861 0.0548 0.0203 0.8768 17.500 1.0280 0.06640 0.06041 0.0548 0.0201 0.8824 18.000 1.0475 0.06971 0.06386 0.0549 0.0197 0.8942 18.250 1.0567 0.07146 0.06572 0.0550 0.0197 0.9012 18.500 1.0726 0.07267 0.06698 0.0551 0.0193 0.9073 18.750 1.0744 0.07523 0.06972 0.0551 0.0192 0.9160 19.000 1.0661 0.07882 0.07354 0.0548 0.0190 0.9278 19.250 1.0738 0.08120 0.07606 0.0542 0.0191 0.9399