XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0710 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.6698 0.09315 0.09054 -0.0382 1.0000 0.0246 -12.750 -0.7743 0.06333 0.06047 -0.0582 1.0000 0.0226 -12.500 -0.8190 0.05489 0.05182 -0.0622 1.0000 0.0223 -12.250 -0.8594 0.04925 0.04598 -0.0619 1.0000 0.0221 -12.000 -0.8977 0.04593 0.04252 -0.0576 1.0000 0.0219 -11.750 -0.9278 0.04126 0.03756 -0.0561 1.0000 0.0217 -11.500 -0.9385 0.03686 0.03279 -0.0558 1.0000 0.0218 -11.250 -0.9352 0.03345 0.02904 -0.0556 1.0000 0.0219 -11.000 -0.9241 0.03070 0.02599 -0.0556 1.0000 0.0221 -10.750 -0.9081 0.02844 0.02346 -0.0557 1.0000 0.0224 -10.500 -0.8892 0.02648 0.02125 -0.0559 1.0000 0.0228 -10.250 -0.8681 0.02485 0.01940 -0.0560 1.0000 0.0232 -10.000 -0.8456 0.02352 0.01787 -0.0562 1.0000 0.0236 -9.750 -0.8218 0.02267 0.01685 -0.0563 1.0000 0.0240 -9.500 -0.7984 0.02073 0.01478 -0.0568 1.0000 0.0249 -9.250 -0.7738 0.01994 0.01397 -0.0570 1.0000 0.0256 -9.000 -0.7483 0.01923 0.01321 -0.0573 1.0000 0.0263 -8.750 -0.7219 0.01854 0.01245 -0.0577 1.0000 0.0271 -8.500 -0.6949 0.01788 0.01172 -0.0581 1.0000 0.0281 -8.250 -0.6675 0.01734 0.01109 -0.0586 1.0000 0.0290 -8.000 -0.6374 0.01627 0.00997 -0.0599 1.0000 0.0306 -7.750 -0.6064 0.01577 0.00949 -0.0612 0.9997 0.0323 -7.500 -0.5730 0.01539 0.00907 -0.0628 0.9989 0.0346 -7.250 -0.5387 0.01472 0.00838 -0.0648 0.9984 0.0376 -7.000 -0.5050 0.01442 0.00809 -0.0665 0.9976 0.0408 -6.750 -0.4711 0.01413 0.00776 -0.0681 0.9968 0.0436 -6.500 -0.4362 0.01361 0.00727 -0.0703 0.9963 0.0478 -6.250 -0.4025 0.01341 0.00704 -0.0719 0.9957 0.0513 -6.000 -0.3673 0.01299 0.00664 -0.0740 0.9953 0.0561 -5.750 -0.3330 0.01279 0.00645 -0.0757 0.9947 0.0612 -5.500 -0.2976 0.01247 0.00616 -0.0777 0.9944 0.0685 -5.250 -0.2624 0.01224 0.00595 -0.0797 0.9939 0.0777 -5.000 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0.00795 0.00410 -0.1197 0.9193 0.7281 0.000 0.5173 0.00783 0.00398 -0.1197 0.8994 0.7300 0.250 0.5455 0.00781 0.00392 -0.1192 0.8689 0.7320 0.500 0.5712 0.00798 0.00382 -0.1180 0.7825 0.7342 0.750 0.5834 0.00943 0.00409 -0.1144 0.5387 0.7367 1.000 0.6020 0.01068 0.00446 -0.1130 0.3471 0.7393 1.250 0.6253 0.01164 0.00477 -0.1124 0.2068 0.7420 1.500 0.6494 0.01231 0.00505 -0.1118 0.1262 0.7440 1.750 0.6747 0.01276 0.00535 -0.1113 0.0940 0.7457 2.000 0.7010 0.01312 0.00565 -0.1109 0.0783 0.7475 2.250 0.7273 0.01351 0.00599 -0.1105 0.0682 0.7495 2.500 0.7541 0.01380 0.00626 -0.1102 0.0618 0.7520 2.750 0.7808 0.01422 0.00667 -0.1099 0.0566 0.7548 3.000 0.8088 0.01449 0.00694 -0.1100 0.0528 0.7576 3.250 0.8343 0.01502 0.00744 -0.1095 0.0481 0.7595 3.500 0.8608 0.01525 0.00772 -0.1091 0.0455 0.7611 3.750 0.8869 0.01555 0.00804 -0.1087 0.0424 0.7628 4.000 0.9110 0.01623 0.00872 -0.1079 0.0392 0.7648 4.250 0.9375 0.01655 0.00909 -0.1075 0.0368 0.7669 4.500 0.9635 0.01697 0.00950 -0.1071 0.0344 0.7693 4.750 0.9873 0.01791 0.01046 -0.1063 0.0322 0.7718 5.000 1.0142 0.01834 0.01093 -0.1061 0.0306 0.7743 5.250 1.0391 0.01877 0.01140 -0.1054 0.0290 0.7761 5.500 1.0631 0.01933 0.01199 -0.1046 0.0278 0.7780 5.750 1.0845 0.02071 0.01343 -0.1034 0.0266 0.7802 6.000 1.1093 0.02132 0.01416 -0.1027 0.0260 0.7827 6.250 1.1339 0.02212 0.01506 -0.1020 0.0253 0.7851 6.500 1.1585 0.02299 0.01603 -0.1014 0.0246 0.7876 6.750 1.1829 0.02392 0.01704 -0.1007 0.0240 0.7900 7.000 1.2057 0.02480 0.01803 -0.0998 0.0234 0.7917 7.250 1.2281 0.02574 0.01906 -0.0988 0.0230 0.7935 7.500 1.2498 0.02686 0.02026 -0.0978 0.0225 0.7956 7.750 1.2684 0.02923 0.02282 -0.0964 0.0219 0.7977 8.000 1.2876 0.03071 0.02455 -0.0950 0.0215 0.8002 8.250 1.3061 0.03233 0.02643 -0.0934 0.0212 0.8027 8.500 1.1734 0.06493 0.06196 -0.0733 0.0291 0.8025 8.750 1.1804 0.06608 0.06315 -0.0715 0.0284 0.8049 9.000 1.1794 0.06785 0.06501 -0.0689 0.0280 0.8067 9.250 1.1680 0.06982 0.06709 -0.0651 0.0278 0.8087 9.500 1.1543 0.07245 0.06983 -0.0619 0.0276 0.8108 9.750 1.1415 0.07534 0.07280 -0.0598 0.0275 0.8130 10.000 1.1257 0.07910 0.07666 -0.0589 0.0274 0.8152 10.250 1.1082 0.08376 0.08141 -0.0596 0.0273 0.8173 10.500 1.0860 0.09013 0.08788 -0.0627 0.0271 0.8191 10.750 0.8340 0.11667 0.11465 -0.0686 0.0265 0.8078 11.000 1.0436 0.07314 0.07070 -0.0432 0.0212 0.8186 11.250 1.0057 0.08236 0.08006 -0.0475 0.0214 0.8192 11.500 0.9625 0.09449 0.09231 -0.0549 0.0217 0.8192