XFOIL Version 6.96 Calculated polar for: FAUVEL 14% AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.6965 0.07505 0.07055 -0.0120 0.6864 0.0276 -11.500 -0.7341 0.06569 0.06099 -0.0188 0.6833 0.0274 -11.250 -0.7725 0.05907 0.05410 -0.0209 0.6793 0.0274 -10.750 -0.8394 0.05004 0.04439 -0.0156 0.6705 0.0275 -10.500 -0.8591 0.04709 0.04113 -0.0112 0.6654 0.0276 -10.250 -0.8585 0.04504 0.03889 -0.0086 0.6596 0.0278 -10.000 -0.8542 0.04316 0.03683 -0.0063 0.6544 0.0281 -9.750 -0.8459 0.04149 0.03500 -0.0044 0.6490 0.0283 -9.500 -0.8363 0.03980 0.03313 -0.0024 0.6437 0.0287 -9.250 -0.8262 0.03803 0.03109 -0.0004 0.6390 0.0290 -9.000 -0.8141 0.03629 0.02912 0.0014 0.6342 0.0295 -8.750 -0.8009 0.03460 0.02716 0.0033 0.6290 0.0302 -8.500 -0.7873 0.03281 0.02499 0.0052 0.6243 0.0309 -8.250 -0.7720 0.03110 0.02286 0.0071 0.6198 0.0316 -8.000 -0.7537 0.02957 0.02100 0.0087 0.6147 0.0321 -7.750 -0.7318 0.02834 0.01968 0.0095 0.6094 0.0325 -7.500 -0.7096 0.02735 0.01857 0.0104 0.6047 0.0330 -7.250 -0.6864 0.02637 0.01749 0.0112 0.5992 0.0335 -7.000 -0.6629 0.02550 0.01650 0.0121 0.5936 0.0342 -6.750 -0.6391 0.02470 0.01555 0.0129 0.5887 0.0350 -6.500 -0.6146 0.02385 0.01456 0.0136 0.5832 0.0359 -6.250 -0.5895 0.02304 0.01358 0.0144 0.5772 0.0366 -6.000 -0.5643 0.02222 0.01265 0.0150 0.5721 0.0371 -5.750 -0.5389 0.02141 0.01186 0.0156 0.5660 0.0377 -5.500 -0.5137 0.02073 0.01118 0.0162 0.5600 0.0384 -5.250 -0.4888 0.02014 0.01053 0.0169 0.5548 0.0391 -5.000 -0.4634 0.01959 0.00997 0.0176 0.5477 0.0403 -4.750 -0.4383 0.01907 0.00938 0.0183 0.5411 0.0414 -4.500 -0.4131 0.01858 0.00882 0.0191 0.5349 0.0423 -4.250 -0.3888 0.01800 0.00827 0.0199 0.5277 0.0431 -4.000 -0.3645 0.01753 0.00778 0.0208 0.5217 0.0442 -3.750 -0.3397 0.01711 0.00737 0.0215 0.5138 0.0453 -3.500 -0.3150 0.01673 0.00693 0.0224 0.5064 0.0466 -3.000 -0.2651 0.01604 0.00620 0.0239 0.4912 0.0509 -2.750 -0.2398 0.01576 0.00587 0.0247 0.4846 0.0537 -2.500 -0.2145 0.01546 0.00558 0.0254 0.4768 0.0572 -2.250 -0.1893 0.01520 0.00527 0.0262 0.4700 0.0631 -2.000 -0.1642 0.01490 0.00504 0.0269 0.4623 0.0755 -1.750 -0.1399 0.01456 0.00477 0.0277 0.4553 0.1024 -1.500 -0.1182 0.01401 0.00455 0.0289 0.4494 0.1715 -1.250 -0.0951 0.01366 0.00444 0.0298 0.4430 0.2454 -1.000 -0.0714 0.01341 0.00428 0.0308 0.4371 0.2878 -0.750 -0.0509 0.01294 0.00410 0.0322 0.4316 0.3659 -0.500 -0.0469 0.01151 0.00407 0.0372 0.4266 0.6965 -0.250 -0.0185 0.01144 0.00428 0.0380 0.4206 0.7891 0.000 0.0129 0.01161 0.00447 0.0382 0.4157 0.8384 0.250 0.0470 0.01182 0.00471 0.0378 0.4099 0.8664 0.500 0.0804 0.01206 0.00489 0.0373 0.4043 0.8853 0.750 0.1091 0.01223 0.00494 0.0376 0.3995 0.8975 1.000 0.1443 0.01240 0.00506 0.0365 0.3942 0.9038 1.250 0.1702 0.01251 0.00512 0.0372 0.3896 0.9131 1.500 0.2070 0.01269 0.00522 0.0357 0.3849 0.9171 1.750 0.2403 0.01288 0.00529 0.0349 0.3808 0.9225 2.000 0.2680 0.01299 0.00540 0.0351 0.3762 0.9298 2.250 0.3060 0.01315 0.00553 0.0333 0.3712 0.9330 2.500 0.3409 0.01331 0.00562 0.0320 0.3671 0.9368 2.750 0.3684 0.01347 0.00569 0.0322 0.3638 0.9428 3.000 0.4046 0.01363 0.00585 0.0306 0.3595 0.9462 3.250 0.4415 0.01378 0.00600 0.0289 0.3549 0.9496 3.500 0.4737 0.01393 0.00612 0.0281 0.3509 0.9547 3.750 0.5048 0.01410 0.00623 0.0275 0.3475 0.9591 4.000 0.5393 0.01426 0.00637 0.0261 0.3442 0.9615 4.250 0.5718 0.01440 0.00655 0.0252 0.3403 0.9647 4.500 0.6009 0.01454 0.00670 0.0249 0.3362 0.9690 4.750 0.6328 0.01469 0.00683 0.0240 0.3326 0.9719 5.000 0.6661 0.01486 0.00695 0.0228 0.3295 0.9745 5.250 0.6982 0.01504 0.00717 0.0218 0.3259 0.9777 5.500 0.7278 0.01520 0.00740 0.0213 0.3214 0.9816 5.750 0.7610 0.01531 0.00751 0.0201 0.3163 0.9841 6.000 0.7938 0.01546 0.00760 0.0189 0.3113 0.9868 6.250 0.8259 0.01559 0.00784 0.0178 0.3052 0.9899 6.500 0.8569 0.01574 0.00802 0.0169 0.3001 0.9930 6.750 0.8897 0.01591 0.00814 0.0157 0.2959 0.9955 7.000 0.9223 0.01609 0.00844 0.0144 0.2911 0.9982 7.250 0.9518 0.01629 0.00870 0.0138 0.2865 1.0000 7.500 0.9726 0.01649 0.00891 0.0149 0.2824 1.0000 7.750 0.9931 0.01673 0.00916 0.0160 0.2783 1.0000 8.000 1.0138 0.01697 0.00952 0.0171 0.2734 1.0000 8.250 1.0340 0.01722 0.00981 0.0182 0.2686 1.0000 8.500 1.0538 0.01748 0.01007 0.0195 0.2642 1.0000 8.750 1.0736 0.01778 0.01047 0.0206 0.2587 1.0000 9.000 1.0929 0.01807 0.01081 0.0219 0.2525 1.0000 9.250 1.1115 0.01839 0.01115 0.0232 0.2462 1.0000 9.500 1.1298 0.01873 0.01156 0.0245 0.2377 1.0000 9.750 1.1469 0.01913 0.01198 0.0258 0.2282 1.0000 10.000 1.1625 0.01961 0.01244 0.0273 0.2177 1.0000 10.250 1.1777 0.02015 0.01301 0.0288 0.2063 1.0000 10.500 1.1917 0.02076 0.01365 0.0304 0.1962 1.0000 10.750 1.2034 0.02148 0.01437 0.0322 0.1868 1.0000 11.000 1.2128 0.02232 0.01521 0.0341 0.1769 1.0000 11.250 1.2200 0.02327 0.01618 0.0360 0.1676 1.0000 11.500 1.2219 0.02447 0.01739 0.0383 0.1595 1.0000 11.750 1.2161 0.02589 0.01883 0.0411 0.1530 1.0000 12.000 1.2043 0.02842 0.02140 0.0420 0.1479 1.0000 12.250 1.1995 0.03093 0.02395 0.0421 0.1422 1.0000 12.500 1.1913 0.03379 0.02683 0.0422 0.1371 1.0000 12.750 1.1856 0.03651 0.02959 0.0422 0.1328 1.0000 13.000 1.1794 0.03934 0.03246 0.0420 0.1284 1.0000 13.250 1.1704 0.04254 0.03569 0.0417 0.1245 1.0000 13.500 1.1638 0.04559 0.03879 0.0413 0.1209 1.0000 13.750 1.1582 0.04866 0.04192 0.0408 0.1170 1.0000 14.000 1.1507 0.05199 0.04529 0.0401 0.1136 1.0000 14.250 1.1419 0.05554 0.04884 0.0393 0.1104 1.0000 14.500 1.1396 0.05859 0.05199 0.0385 0.1069 1.0000 14.750 1.1349 0.06202 0.05546 0.0375 0.1033 1.0000 15.000 1.1284 0.06570 0.05916 0.0363 0.0999 1.0000 15.250 1.1251 0.06909 0.06262 0.0353 0.0965 1.0000 15.500 1.1215 0.07258 0.06619 0.0341 0.0929 1.0000 15.750 1.1153 0.07644 0.07007 0.0328 0.0894 1.0000 16.000 1.1117 0.08003 0.07371 0.0315 0.0862 1.0000 16.250 1.1078 0.08374 0.07748 0.0302 0.0827 1.0000 16.500 1.1026 0.08763 0.08139 0.0287 0.0797 1.0000 16.750 1.0987 0.09141 0.08522 0.0273 0.0767 1.0000