XFOIL Version 6.96 Calculated polar for: ONERA NACA CAMBRE AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4552 0.09251 0.08743 -0.0210 1.0000 0.0434 -10.000 -0.6236 0.08141 0.07593 -0.0304 1.0000 0.0385 -9.750 -0.6217 0.07805 0.07258 -0.0309 1.0000 0.0382 -9.500 -0.6291 0.07415 0.06865 -0.0318 1.0000 0.0378 -9.250 -0.6405 0.07041 0.06486 -0.0317 1.0000 0.0375 -9.000 -0.6505 0.06665 0.06098 -0.0311 1.0000 0.0371 -8.750 -0.6574 0.06280 0.05697 -0.0303 1.0000 0.0366 -8.500 -0.6616 0.05898 0.05296 -0.0291 1.0000 0.0362 -8.250 -0.6630 0.05527 0.04900 -0.0276 1.0000 0.0359 -8.000 -0.6612 0.05179 0.04526 -0.0258 1.0000 0.0358 -7.750 -0.6568 0.04862 0.04179 -0.0239 1.0000 0.0362 -7.500 -0.6505 0.04562 0.03846 -0.0218 1.0000 0.0367 -7.250 -0.6423 0.04280 0.03529 -0.0195 1.0000 0.0371 -7.000 -0.6318 0.04017 0.03233 -0.0173 1.0000 0.0372 -6.750 -0.6195 0.03773 0.02955 -0.0152 1.0000 0.0371 -6.500 -0.6054 0.03547 0.02698 -0.0131 1.0000 0.0371 -6.250 -0.5896 0.03343 0.02462 -0.0111 1.0000 0.0373 -6.000 -0.5725 0.03155 0.02245 -0.0093 1.0000 0.0375 -5.750 -0.5542 0.02986 0.02047 -0.0076 1.0000 0.0378 -5.500 -0.5350 0.02841 0.01870 -0.0059 1.0000 0.0384 -5.250 -0.5156 0.02701 0.01727 -0.0046 1.0000 0.0395 -5.000 -0.4958 0.02597 0.01621 -0.0034 1.0000 0.0409 -4.750 -0.4754 0.02492 0.01508 -0.0021 1.0000 0.0421 -4.500 -0.4544 0.02386 0.01391 -0.0008 1.0000 0.0430 -4.250 -0.4335 0.02290 0.01286 0.0006 1.0000 0.0439 -4.000 -0.4129 0.02205 0.01194 0.0019 1.0000 0.0449 -3.750 -0.3842 0.02111 0.01103 0.0015 0.9969 0.0466 -3.500 -0.3480 0.02027 0.01025 -0.0006 0.9904 0.0498 -3.250 -0.3109 0.01952 0.00947 -0.0027 0.9837 0.0529 -3.000 -0.2768 0.01872 0.00869 -0.0042 0.9752 0.0557 -2.750 -0.2407 0.01812 0.00806 -0.0061 0.9669 0.0612 -2.500 -0.2037 0.01751 0.00747 -0.0082 0.9584 0.0686 -2.250 -0.1681 0.01696 0.00692 -0.0097 0.9476 0.0810 -2.000 -0.1365 0.01556 0.00625 -0.0110 0.9358 0.2043 -1.750 -0.1158 0.01357 0.00623 -0.0095 0.9236 0.6430 -1.500 -0.0857 0.01330 0.00639 -0.0083 0.9106 0.7672 -1.250 -0.0522 0.01338 0.00662 -0.0076 0.8975 0.8435 -1.000 -0.0117 0.01363 0.00688 -0.0084 0.8849 0.8966 -0.750 0.0296 0.01368 0.00679 -0.0103 0.8679 0.9151 -0.500 0.0674 0.01362 0.00659 -0.0117 0.8473 0.9278 -0.250 0.1038 0.01359 0.00641 -0.0129 0.8247 0.9395 0.000 0.1434 0.01355 0.00623 -0.0148 0.8022 0.9482 0.250 0.1799 0.01353 0.00607 -0.0163 0.7774 0.9581 0.500 0.2185 0.01352 0.00589 -0.0181 0.7489 0.9662 0.750 0.2554 0.01352 0.00572 -0.0197 0.7181 0.9745 1.000 0.2914 0.01356 0.00560 -0.0213 0.6885 0.9832 1.250 0.3300 0.01359 0.00547 -0.0234 0.6599 0.9903 1.500 0.3685 0.01365 0.00538 -0.0257 0.6312 0.9979 1.750 0.3953 0.01373 0.00533 -0.0256 0.6041 1.0000 2.000 0.4178 0.01384 0.00530 -0.0246 0.5790 1.0000 2.250 0.4400 0.01398 0.00531 -0.0236 0.5536 1.0000 2.500 0.4622 0.01414 0.00534 -0.0226 0.5268 1.0000 2.750 0.4841 0.01434 0.00539 -0.0215 0.5009 1.0000 3.000 0.5061 0.01455 0.00549 -0.0205 0.4762 1.0000 3.250 0.5279 0.01479 0.00560 -0.0194 0.4533 1.0000 3.500 0.5500 0.01502 0.00576 -0.0184 0.4299 1.0000 3.750 0.5718 0.01529 0.00593 -0.0173 0.4073 1.0000 4.000 0.5935 0.01557 0.00613 -0.0162 0.3853 1.0000 4.250 0.6150 0.01588 0.00634 -0.0151 0.3639 1.0000 4.500 0.6363 0.01623 0.00658 -0.0140 0.3436 1.0000 4.750 0.6576 0.01660 0.00687 -0.0129 0.3244 1.0000 5.000 0.6792 0.01695 0.00717 -0.0119 0.3059 1.0000 5.250 0.7005 0.01733 0.00750 -0.0108 0.2897 1.0000 5.500 0.7217 0.01774 0.00785 -0.0097 0.2747 1.0000 5.750 0.7428 0.01818 0.00824 -0.0086 0.2609 1.0000 6.000 0.7644 0.01860 0.00868 -0.0076 0.2476 1.0000 6.250 0.7859 0.01905 0.00913 -0.0066 0.2349 1.0000 6.500 0.8072 0.01953 0.00961 -0.0055 0.2232 1.0000 6.750 0.8281 0.02005 0.01009 -0.0045 0.2127 1.0000 7.000 0.8496 0.02056 0.01065 -0.0035 0.2028 1.0000 7.250 0.8708 0.02113 0.01123 -0.0026 0.1938 1.0000 7.500 0.8916 0.02172 0.01183 -0.0016 0.1854 1.0000 7.750 0.9130 0.02232 0.01250 -0.0007 0.1770 1.0000 8.000 0.9336 0.02296 0.01314 0.0003 0.1700 1.0000 8.250 0.9549 0.02363 0.01393 0.0012 0.1635 1.0000 8.500 0.9756 0.02430 0.01467 0.0022 0.1575 1.0000 8.750 0.9960 0.02505 0.01545 0.0031 0.1520 1.0000 9.000 1.0165 0.02578 0.01631 0.0040 0.1460 1.0000 9.250 1.0360 0.02654 0.01708 0.0050 0.1410 1.0000 9.500 1.0553 0.02731 0.01803 0.0060 0.1346 1.0000 9.750 1.0729 0.02799 0.01875 0.0071 0.1279 1.0000 10.000 1.0901 0.02876 0.01967 0.0083 0.1209 1.0000 10.250 1.1061 0.02948 0.02048 0.0095 0.1143 1.0000 10.500 1.1216 0.03032 0.02147 0.0108 0.1078 1.0000 10.750 1.1356 0.03112 0.02238 0.0122 0.1014 1.0000 11.000 1.1486 0.03209 0.02349 0.0137 0.0956 1.0000 11.250 1.1599 0.03306 0.02462 0.0152 0.0897 1.0000 11.500 1.1675 0.03419 0.02585 0.0172 0.0847 1.0000 11.750 1.1742 0.03542 0.02726 0.0192 0.0790 1.0000 12.000 1.1773 0.03687 0.02875 0.0210 0.0745 1.0000 12.250 1.1815 0.03853 0.03064 0.0225 0.0688 1.0000 12.500 1.1813 0.04046 0.03263 0.0237 0.0650 1.0000 12.750 1.1817 0.04275 0.03513 0.0246 0.0605 1.0000 13.000 1.1794 0.04533 0.03785 0.0249 0.0572 1.0000 13.250 1.1740 0.04841 0.04098 0.0247 0.0551 1.0000 13.500 1.1691 0.05188 0.04467 0.0242 0.0525 1.0000 13.750 1.1619 0.05578 0.04874 0.0231 0.0504 1.0000 14.000 1.1529 0.06015 0.05325 0.0213 0.0488 1.0000 14.250 1.1421 0.06498 0.05819 0.0191 0.0476 1.0000 14.500 1.1301 0.07013 0.06343 0.0167 0.0467 1.0000 14.750 1.1155 0.07601 0.06949 0.0139 0.0457 1.0000 15.000 1.0986 0.08248 0.07615 0.0106 0.0449 1.0000 15.250 1.0794 0.08955 0.08341 0.0070 0.0442 1.0000 15.500 1.0581 0.09735 0.09137 0.0030 0.0437 1.0000 15.750 1.0331 0.10616 0.10035 -0.0017 0.0434 1.0000 16.000 1.0004 0.11708 0.11146 -0.0075 0.0433 1.0000 16.250 0.8858 0.14970 0.14424 -0.0245 0.0440 1.0000