XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0410 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -1.0901 0.07627 0.07288 -0.0255 1.0000 0.0128 -15.250 -1.1174 0.06653 0.06291 -0.0322 1.0000 0.0128 -15.000 -1.1357 0.05965 0.05583 -0.0365 1.0000 0.0128 -14.750 -1.1485 0.05434 0.05036 -0.0393 1.0000 0.0129 -14.500 -1.1576 0.04997 0.04583 -0.0412 1.0000 0.0129 -14.250 -1.1632 0.04633 0.04203 -0.0424 1.0000 0.0130 -14.000 -1.1662 0.04317 0.03874 -0.0431 1.0000 0.0130 -13.750 -1.1669 0.04040 0.03583 -0.0435 1.0000 0.0131 -13.500 -1.1654 0.03797 0.03327 -0.0436 1.0000 0.0132 -13.250 -1.1622 0.03578 0.03095 -0.0434 1.0000 0.0133 -13.000 -1.1575 0.03384 0.02888 -0.0430 1.0000 0.0135 -12.750 -1.1518 0.03208 0.02698 -0.0424 1.0000 0.0136 -12.500 -1.1457 0.03049 0.02528 -0.0415 1.0000 0.0137 -12.250 -1.1354 0.02901 0.02367 -0.0410 1.0000 0.0139 -12.000 -1.1213 0.02760 0.02213 -0.0410 1.0000 0.0141 -11.750 -1.1052 0.02631 0.02071 -0.0409 1.0000 0.0143 -11.500 -1.0876 0.02514 0.01942 -0.0407 1.0000 0.0145 -11.250 -1.0690 0.02407 0.01822 -0.0405 1.0000 0.0147 -11.000 -1.0492 0.02307 0.01711 -0.0402 1.0000 0.0149 -10.750 -1.0286 0.02215 0.01608 -0.0400 1.0000 0.0152 -10.500 -1.0070 0.02133 0.01515 -0.0398 1.0000 0.0154 -10.250 -0.9860 0.02031 0.01409 -0.0397 1.0000 0.0158 -10.000 -0.9635 0.01955 0.01327 -0.0396 1.0000 0.0163 -9.750 -0.9402 0.01888 0.01255 -0.0394 1.0000 0.0167 -9.500 -0.9165 0.01823 0.01185 -0.0393 1.0000 0.0171 -9.250 -0.8924 0.01760 0.01116 -0.0392 1.0000 0.0176 -9.000 -0.8680 0.01700 0.01050 -0.0392 1.0000 0.0181 -8.750 -0.8431 0.01643 0.00987 -0.0392 1.0000 0.0187 -8.500 -0.8180 0.01587 0.00925 -0.0392 1.0000 0.0192 -8.250 -0.7926 0.01532 0.00869 -0.0392 1.0000 0.0201 -8.000 -0.7668 0.01486 0.00822 -0.0393 1.0000 0.0211 -7.750 -0.7409 0.01443 0.00776 -0.0393 1.0000 0.0223 -7.500 -0.7148 0.01401 0.00731 -0.0393 1.0000 0.0236 -7.250 -0.6886 0.01362 0.00692 -0.0394 1.0000 0.0254 -7.000 -0.6624 0.01329 0.00658 -0.0394 1.0000 0.0276 -6.750 -0.6360 0.01294 0.00623 -0.0395 1.0000 0.0299 -6.500 -0.6096 0.01264 0.00593 -0.0395 1.0000 0.0324 -6.250 -0.5832 0.01239 0.00565 -0.0395 1.0000 0.0344 -6.000 -0.5565 0.01206 0.00536 -0.0396 1.0000 0.0371 -5.750 -0.5290 0.01181 0.00511 -0.0398 0.9998 0.0397 -5.500 -0.4956 0.01154 0.00482 -0.0412 0.9985 0.0424 -5.250 -0.4622 0.01124 0.00456 -0.0427 0.9971 0.0463 -5.000 -0.4285 0.01103 0.00434 -0.0442 0.9955 0.0502 -4.750 -0.3938 0.01072 0.00409 -0.0460 0.9942 0.0566 -4.500 -0.3601 0.01047 0.00385 -0.0475 0.9918 0.0623 -4.250 -0.3259 0.01019 0.00362 -0.0490 0.9894 0.0697 -4.000 -0.2917 0.00994 0.00341 -0.0506 0.9873 0.0791 -3.750 -0.2571 0.00967 0.00321 -0.0523 0.9856 0.0937 -3.500 -0.2218 0.00934 0.00301 -0.0542 0.9841 0.1198 -3.250 -0.1871 0.00895 0.00282 -0.0561 0.9819 0.1634 -3.000 -0.1525 0.00851 0.00262 -0.0580 0.9790 0.2239 -2.750 -0.1161 0.00792 0.00240 -0.0605 0.9767 0.3162 -2.500 -0.0782 0.00718 0.00214 -0.0635 0.9748 0.4407 -2.250 -0.0408 0.00662 0.00213 -0.0660 0.9729 0.5842 -2.000 -0.0069 0.00656 0.00214 -0.0672 0.9675 0.6161 -1.750 0.0275 0.00652 0.00213 -0.0684 0.9604 0.6336 -1.500 0.0609 0.00652 0.00216 -0.0694 0.9504 0.6535 -1.250 0.0933 0.00654 0.00218 -0.0700 0.9351 0.6666 -1.000 0.1239 0.00656 0.00217 -0.0702 0.9155 0.6749 -0.750 0.1520 0.00661 0.00218 -0.0699 0.8907 0.6800 -0.500 0.1800 0.00671 0.00217 -0.0695 0.8646 0.6862 -0.250 0.2068 0.00684 0.00219 -0.0689 0.8292 0.6916 0.000 0.2333 0.00703 0.00222 -0.0683 0.7824 0.6961 0.250 0.2600 0.00727 0.00223 -0.0677 0.7225 0.6993 0.500 0.2863 0.00765 0.00225 -0.0673 0.6402 0.7018 0.750 0.3113 0.00834 0.00235 -0.0668 0.5003 0.7038 1.000 0.3369 0.00906 0.00253 -0.0667 0.3682 0.7056 1.250 0.3639 0.00952 0.00268 -0.0666 0.2855 0.7073 1.750 0.4186 0.01032 0.00299 -0.0667 0.1632 0.7106 2.000 0.4464 0.01062 0.00315 -0.0667 0.1279 0.7125 2.250 0.4745 0.01088 0.00331 -0.0668 0.1060 0.7144 2.500 0.5027 0.01112 0.00347 -0.0669 0.0878 0.7161 2.750 0.5310 0.01135 0.00365 -0.0670 0.0760 0.7179 3.000 0.5591 0.01159 0.00384 -0.0670 0.0667 0.7196 3.250 0.5874 0.01181 0.00404 -0.0671 0.0609 0.7213 3.500 0.6153 0.01205 0.00425 -0.0671 0.0548 0.7229 3.750 0.6431 0.01226 0.00447 -0.0671 0.0501 0.7244 4.000 0.6707 0.01253 0.00472 -0.0670 0.0461 0.7261 4.250 0.6985 0.01275 0.00498 -0.0669 0.0434 0.7281 4.500 0.7261 0.01300 0.00522 -0.0669 0.0401 0.7302 4.750 0.7536 0.01329 0.00551 -0.0668 0.0373 0.7323 5.000 0.7812 0.01354 0.00579 -0.0668 0.0346 0.7343 5.250 0.8084 0.01386 0.00609 -0.0667 0.0321 0.7363 5.500 0.8358 0.01416 0.00642 -0.0666 0.0300 0.7383 5.750 0.8628 0.01447 0.00676 -0.0664 0.0277 0.7401 6.000 0.8893 0.01484 0.00715 -0.0662 0.0257 0.7420 6.250 0.9160 0.01519 0.00755 -0.0659 0.0241 0.7440 6.500 0.9424 0.01557 0.00797 -0.0657 0.0226 0.7461 6.750 0.9684 0.01603 0.00844 -0.0654 0.0212 0.7484 7.000 0.9946 0.01645 0.00892 -0.0651 0.0203 0.7508 7.250 1.0206 0.01689 0.00941 -0.0648 0.0193 0.7533 7.500 1.0463 0.01737 0.00992 -0.0645 0.0185 0.7556 7.750 1.0714 0.01790 0.01051 -0.0640 0.0179 0.7577 8.000 1.0956 0.01855 0.01122 -0.0635 0.0173 0.7600 8.250 1.1202 0.01914 0.01190 -0.0630 0.0170 0.7628 8.500 1.1445 0.01976 0.01263 -0.0624 0.0166 0.7658 8.750 1.1685 0.02043 0.01339 -0.0618 0.0163 0.7688 9.000 1.1921 0.02113 0.01417 -0.0612 0.0159 0.7717 9.250 1.2151 0.02184 0.01499 -0.0605 0.0156 0.7742 9.500 1.2377 0.02259 0.01586 -0.0598 0.0153 0.7770 9.750 1.2599 0.02337 0.01674 -0.0590 0.0150 0.7800 10.000 1.2815 0.02421 0.01767 -0.0581 0.0148 0.7832 10.250 1.3024 0.02512 0.01868 -0.0572 0.0145 0.7865 10.500 1.3216 0.02617 0.01985 -0.0561 0.0142 0.7893 10.750 1.3384 0.02751 0.02132 -0.0547 0.0139 0.7925 11.000 1.3571 0.02854 0.02252 -0.0535 0.0138 0.7960 11.250 1.3745 0.02968 0.02383 -0.0522 0.0136 0.7997 11.500 1.3900 0.03097 0.02530 -0.0507 0.0134 0.8033 11.750 1.4037 0.03236 0.02689 -0.0490 0.0133 0.8070 12.000 1.4153 0.03386 0.02861 -0.0471 0.0131 0.8111 12.250 1.4246 0.03549 0.03043 -0.0450 0.0130 0.8154 12.500 1.4307 0.03721 0.03236 -0.0426 0.0128 0.8192 12.750 1.4303 0.03900 0.03434 -0.0393 0.0127 0.8235 13.000 1.4264 0.04099 0.03653 -0.0359 0.0127 0.8283 13.250 1.4208 0.04337 0.03912 -0.0331 0.0126 0.8329 13.500 1.4129 0.04616 0.04212 -0.0309 0.0125 0.8376 13.750 1.4020 0.04960 0.04577 -0.0296 0.0124 0.8426 14.000 1.3880 0.05386 0.05026 -0.0295 0.0124 0.8474 14.250 1.3688 0.05948 0.05612 -0.0310 0.0124 0.8521 14.500 1.3429 0.06744 0.06435 -0.0355 0.0124 0.8568 14.750 1.2962 0.08272 0.07998 -0.0472 0.0125 0.8597