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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9012 0.07101 0.06666 -0.1106 0.8986 0.0173 -19.500 -0.9028 0.06802 0.06352 -0.1113 0.8892 0.0173 -19.250 -0.9047 0.06516 0.06050 -0.1116 0.8807 0.0174 -19.000 -0.9055 0.06242 0.05764 -0.1118 0.8742 0.0176 -18.750 -0.9038 0.06006 0.05518 -0.1119 0.8673 0.0178 -18.500 -0.9004 0.05788 0.05290 -0.1121 0.8607 0.0179 -18.250 -0.8952 0.05585 0.05078 -0.1122 0.8554 0.0178 -18.000 -0.8908 0.05384 0.04869 -0.1122 0.8497 0.0180 -17.750 -0.8849 0.05202 0.04679 -0.1122 0.8440 0.0181 -17.500 -0.8788 0.05019 0.04489 -0.1122 0.8398 0.0183 -17.250 -0.8718 0.04848 0.04311 -0.1120 0.8353 0.0183 -17.000 -0.8638 0.04692 0.04148 -0.1119 0.8306 0.0186 -16.750 -0.8558 0.04542 0.03990 -0.1116 0.8259 0.0187 -16.500 -0.8472 0.04395 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0.7058 0.7246 2.500 0.4587 0.00853 0.00431 -0.0447 0.7037 0.7253 2.750 0.4892 0.00843 0.00421 -0.0456 0.7014 0.7259 3.000 0.5194 0.00841 0.00418 -0.0463 0.6992 0.7265 3.250 0.5487 0.00849 0.00427 -0.0470 0.6966 0.7271 3.500 0.5751 0.00836 0.00420 -0.0470 0.6939 0.7278 3.750 0.6025 0.00824 0.00410 -0.0471 0.6900 0.7285 4.000 0.6314 0.00810 0.00397 -0.0476 0.6856 0.7293 4.250 0.6611 0.00803 0.00388 -0.0482 0.6808 0.7301 4.500 0.6850 0.00793 0.00383 -0.0476 0.6752 0.7309 4.750 0.7098 0.00781 0.00373 -0.0472 0.6678 0.7316 5.000 0.7331 0.00773 0.00366 -0.0465 0.6585 0.7324 5.250 0.7549 0.00769 0.00361 -0.0455 0.6475 0.7332 5.500 0.7742 0.00768 0.00362 -0.0440 0.6319 0.7341 5.750 0.7762 0.00780 0.00362 -0.0390 0.5921 0.7351 6.000 0.7522 0.00836 0.00398 -0.0290 0.5527 0.7364 6.250 0.7308 0.00933 0.00475 -0.0203 0.5110 0.7376 6.500 0.7159 0.01037 0.00562 -0.0133 0.4738 0.7386 6.750 0.7007 0.01160 0.00667 -0.0066 0.4334 0.7394 7.000 0.6922 0.01272 0.00763 -0.0013 0.3971 0.7411 7.250 0.6852 0.01388 0.00864 0.0036 0.3595 0.7429 7.500 0.6828 0.01496 0.00956 0.0076 0.3238 0.7444 7.750 0.6800 0.01611 0.01053 0.0115 0.2838 0.7459 8.000 0.6818 0.01715 0.01141 0.0147 0.2489 0.7472 8.250 0.6838 0.01822 0.01228 0.0177 0.2090 0.7485 8.500 0.6878 0.01926 0.01315 0.0204 0.1739 0.7499 8.750 0.6919 0.02032 0.01402 0.0229 0.1370 0.7512 9.000 0.6972 0.02138 0.01488 0.0253 0.1015 0.7526 9.250 0.7039 0.02241 0.01576 0.0273 0.0741 0.7540 9.500 0.7135 0.02333 0.01655 0.0290 0.0533 0.7554 9.750 0.7265 0.02412 0.01726 0.0302 0.0421 0.7566 10.000 0.7413 0.02483 0.01794 0.0312 0.0369 0.7577 10.250 0.7561 0.02555 0.01865 0.0322 0.0334 0.7589 10.500 0.7704 0.02628 0.01938 0.0332 0.0306 0.7612 10.750 0.7872 0.02688 0.02002 0.0338 0.0289 0.7632 11.000 0.8009 0.02768 0.02082 0.0349 0.0266 0.7651 11.250 0.8169 0.02838 0.02155 0.0356 0.0255 0.7669 11.500 0.8314 0.02917 0.02237 0.0364 0.0238 0.7687 11.750 0.8449 0.03005 0.02326 0.0373 0.0224 0.7705 12.000 0.8612 0.03077 0.02401 0.0379 0.0214 0.7724 12.250 0.8761 0.03159 0.02485 0.0385 0.0209 0.7742 12.500 0.8892 0.03253 0.02581 0.0393 0.0200 0.7758 12.750 0.9008 0.03361 0.02690 0.0402 0.0195 0.7773 13.000 0.9145 0.03453 0.02787 0.0409 0.0188 0.7801 13.250 0.9284 0.03543 0.02883 0.0416 0.0182 0.7829 13.500 0.9410 0.03646 0.02992 0.0423 0.0181 0.7854 13.750 0.9534 0.03752 0.03103 0.0430 0.0178 0.7880 14.000 0.9663 0.03857 0.03210 0.0435 0.0171 0.7906 14.250 0.9762 0.03987 0.03343 0.0443 0.0166 0.7930 14.500 0.9853 0.04127 0.03488 0.0450 0.0166 0.7953 14.750 0.9901 0.04303 0.03669 0.0460 0.0162 0.7975 15.000 0.9998 0.04440 0.03814 0.0466 0.0161 0.8012 15.250 1.0124 0.04556 0.03937 0.0470 0.0158 0.8046 15.500 1.0213 0.04706 0.04094 0.0475 0.0157 0.8078 15.750 1.0299 0.04863 0.04257 0.0480 0.0155 0.8111 16.000 1.0384 0.05026 0.04426 0.0484 0.0154 0.8141 16.250 1.0459 0.05200 0.04606 0.0487 0.0153 0.8171 16.500 1.0553 0.05356 0.04769 0.0490 0.0149 0.8213 16.750 1.0618 0.05542 0.04964 0.0493 0.0148 0.8252 17.000 1.0662 0.05753 0.05183 0.0495 0.0149 0.8292 17.250 1.0733 0.05946 0.05382 0.0496 0.0147 0.8330 17.500 1.0799 0.06147 0.05590 0.0496 0.0145 0.8371 17.750 1.0862 0.06349 0.05800 0.0495 0.0144 0.8421 18.000 1.0897 0.06587 0.06046 0.0495 0.0142 0.8471 18.250 1.0933 0.06831 0.06297 0.0492 0.0142 0.8515 18.500 1.0975 0.07066 0.06541 0.0490 0.0141 0.8571 18.750 1.0996 0.07330 0.06813 0.0487 0.0139 0.8629 19.000 1.0976 0.07643 0.07134 0.0483 0.0136 0.8684 19.250 1.1029 0.07880 0.07381 0.0478 0.0138 0.8753