XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0712 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 -1.1395 0.09761 0.09444 -0.0430 1.0000 0.0141 -19.500 -1.1797 0.08649 0.08314 -0.0492 1.0000 0.0141 -19.250 -1.2093 0.07749 0.07397 -0.0543 1.0000 0.0141 -19.000 -1.2303 0.07016 0.06649 -0.0585 1.0000 0.0142 -18.750 -1.2445 0.06421 0.06041 -0.0618 1.0000 0.0142 -18.500 -1.2581 0.05861 0.05467 -0.0649 1.0000 0.0143 -18.250 -1.2683 0.05384 0.04979 -0.0673 1.0000 0.0144 -18.000 -1.2744 0.04985 0.04570 -0.0691 1.0000 0.0145 -17.750 -1.2781 0.04638 0.04212 -0.0704 1.0000 0.0146 -17.500 -1.2790 0.04342 0.03908 -0.0714 1.0000 0.0147 -17.250 -1.2780 0.04085 0.03643 -0.0720 1.0000 0.0149 -17.000 -1.2756 0.03857 0.03407 -0.0724 1.0000 0.0150 -16.750 -1.2718 0.03652 0.03195 -0.0725 1.0000 0.0152 -16.500 -1.2667 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0.6579 2.750 0.8386 0.01157 0.00436 -0.1239 0.0506 0.6598 3.000 0.8662 0.01178 0.00455 -0.1237 0.0470 0.6618 3.250 0.8937 0.01200 0.00474 -0.1236 0.0440 0.6638 3.500 0.9211 0.01222 0.00495 -0.1234 0.0411 0.6656 3.750 0.9483 0.01246 0.00517 -0.1231 0.0388 0.6673 4.000 0.9756 0.01269 0.00538 -0.1229 0.0370 0.6688 4.250 1.0026 0.01293 0.00562 -0.1227 0.0350 0.6708 4.500 1.0294 0.01320 0.00589 -0.1223 0.0334 0.6728 4.750 1.0563 0.01343 0.00614 -0.1221 0.0324 0.6747 5.000 1.0830 0.01368 0.00641 -0.1217 0.0312 0.6767 5.250 1.1094 0.01396 0.00669 -0.1213 0.0299 0.6788 5.500 1.1354 0.01428 0.00700 -0.1209 0.0285 0.6808 5.750 1.1617 0.01454 0.00729 -0.1205 0.0278 0.6829 6.000 1.1878 0.01483 0.00759 -0.1201 0.0270 0.6848 6.500 1.2392 0.01545 0.00824 -0.1190 0.0252 0.6891 6.750 1.2642 0.01583 0.00863 -0.1184 0.0243 0.6915 7.000 1.2896 0.01614 0.00899 -0.1179 0.0238 0.6940 7.250 1.3146 0.01648 0.00935 -0.1172 0.0232 0.6965 7.500 1.3394 0.01682 0.00973 -0.1166 0.0225 0.6992 7.750 1.3639 0.01719 0.01011 -0.1159 0.0218 0.7016 8.000 1.3881 0.01759 0.01051 -0.1151 0.0211 0.7037 8.250 1.4115 0.01804 0.01099 -0.1143 0.0203 0.7060 8.500 1.4354 0.01842 0.01142 -0.1135 0.0200 0.7082 8.750 1.4588 0.01883 0.01188 -0.1126 0.0195 0.7104 9.000 1.4818 0.01925 0.01235 -0.1116 0.0191 0.7127 9.250 1.5044 0.01970 0.01283 -0.1106 0.0186 0.7151 9.500 1.5266 0.02017 0.01334 -0.1096 0.0182 0.7174 9.750 1.5482 0.02067 0.01386 -0.1084 0.0178 0.7195 10.000 1.5690 0.02122 0.01444 -0.1071 0.0173 0.7214 10.250 1.5889 0.02183 0.01511 -0.1057 0.0169 0.7236 10.500 1.6091 0.02235 0.01570 -0.1043 0.0167 0.7259 10.750 1.6285 0.02290 0.01632 -0.1028 0.0165 0.7283 11.000 1.6470 0.02347 0.01696 -0.1012 0.0163 0.7307 11.250 1.6643 0.02408 0.01763 -0.0993 0.0160 0.7332 11.500 1.6806 0.02470 0.01831 -0.0973 0.0158 0.7357 11.750 1.6956 0.02535 0.01902 -0.0951 0.0156 0.7380 12.000 1.7074 0.02602 0.01976 -0.0923 0.0153 0.7403 12.250 1.7194 0.02675 0.02057 -0.0897 0.0151 0.7427 12.500 1.7316 0.02755 0.02144 -0.0872 0.0149 0.7451 12.750 1.7431 0.02840 0.02237 -0.0847 0.0148 0.7474 13.000 1.7537 0.02934 0.02338 -0.0821 0.0146 0.7498 13.250 1.7634 0.03036 0.02447 -0.0796 0.0144 0.7523 13.500 1.7714 0.03152 0.02571 -0.0769 0.0142 0.7547 13.750 1.7769 0.03288 0.02716 -0.0741 0.0139 0.7569 14.000 1.7844 0.03412 0.02850 -0.0716 0.0138 0.7592 14.250 1.7919 0.03538 0.02987 -0.0693 0.0138 0.7616 14.500 1.7983 0.03676 0.03135 -0.0670 0.0136 0.7640 14.750 1.8033 0.03830 0.03299 -0.0647 0.0136 0.7664 15.000 1.8067 0.04003 0.03482 -0.0625 0.0135 0.7687 15.250 1.8092 0.04188 0.03678 -0.0604 0.0134 0.7709 15.500 1.8104 0.04394 0.03896 -0.0584 0.0133 0.7729 15.750 1.8099 0.04624 0.04138 -0.0567 0.0132 0.7751 16.000 1.8082 0.04876 0.04403 -0.0551 0.0131 0.7772 16.250 1.8045 0.05161 0.04700 -0.0538 0.0130 0.7793 16.500 1.7990 0.05484 0.05037 -0.0529 0.0130 0.7814 16.750 1.7915 0.05850 0.05416 -0.0524 0.0129 0.7834 17.000 1.7820 0.06268 0.05848 -0.0525 0.0128 0.7853 17.250 1.7694 0.06765 0.06360 -0.0534 0.0128 0.7871 17.750 1.7313 0.08105 0.07734 -0.0586 0.0127 0.7899 18.000 1.7009 0.09065 0.08715 -0.0636 0.0127 0.7909 18.250 1.6548 0.10405 0.10080 -0.0716 0.0127 0.7913 18.500 1.5745 0.12499 0.12208 -0.0844 0.0129 0.7902