XFOIL Version 6.96 Calculated polar for: RONCZ 1080 VOYAGER INNER AFT WING 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 ------ -------- --------- --------- -------- -------- -------- -14.000 -0.2942 0.10695 0.10215 -0.0862 0.7604 0.0164 -13.750 -0.3571 0.08714 0.08235 -0.0951 0.7619 0.0161 -13.500 -0.4177 0.06991 0.06490 -0.1061 0.7602 0.0154 -13.000 -0.4883 0.05450 0.04892 -0.1141 0.7509 0.0148 -12.750 -0.5040 0.05086 0.04507 -0.1145 0.7454 0.0151 -12.500 -0.5227 0.04713 0.04106 -0.1139 0.7405 0.0150 -12.250 -0.5321 0.04457 0.03827 -0.1129 0.7360 0.0152 -12.000 -0.5429 0.04192 0.03535 -0.1112 0.7313 0.0155 -11.750 -0.5493 0.03959 0.03275 -0.1093 0.7270 0.0155 -11.500 -0.5534 0.03750 0.03036 -0.1071 0.7231 0.0158 -11.250 -0.5534 0.03560 0.02816 -0.1049 0.7198 0.0160 -11.000 -0.5491 0.03388 0.02621 -0.1029 0.7161 0.0161 -10.750 -0.5419 0.03228 0.02435 -0.1011 0.7125 0.0163 -10.500 -0.5309 0.03090 0.02274 -0.0995 0.7092 0.0164 -10.250 -0.5174 0.02960 0.02132 -0.0982 0.7061 0.0167 -10.000 -0.5025 0.02854 0.02013 -0.0969 0.7033 0.0170 -9.750 -0.4866 0.02755 0.01905 -0.0958 0.7004 0.0172 -9.500 -0.4703 0.02663 0.01804 -0.0946 0.6974 0.0175 -9.250 -0.4531 0.02573 0.01705 -0.0935 0.6947 0.0180 -9.000 -0.4355 0.02487 0.01606 -0.0924 0.6922 0.0186 -8.750 -0.4176 0.02406 0.01514 -0.0912 0.6900 0.0191 -8.500 -0.3998 0.02333 0.01428 -0.0900 0.6879 0.0195 -8.250 -0.3834 0.02261 0.01350 -0.0886 0.6861 0.0202 -8.000 -0.3669 0.02207 0.01295 -0.0872 0.6841 0.0213 -7.750 -0.3503 0.02152 0.01234 -0.0857 0.6820 0.0222 -7.500 -0.3333 0.02103 0.01177 -0.0842 0.6799 0.0234 -7.250 -0.3180 0.02049 0.01122 -0.0825 0.6779 0.0247 -7.000 -0.3011 0.02002 0.01071 -0.0809 0.6760 0.0260 -6.750 -0.2831 0.01956 0.01017 -0.0795 0.6740 0.0277 -6.500 -0.2650 0.01909 0.00967 -0.0781 0.6722 0.0300 -6.250 -0.2462 0.01866 0.00920 -0.0768 0.6705 0.0336 -6.000 -0.2268 0.01826 0.00878 -0.0756 0.6690 0.0394 -5.750 -0.2078 0.01785 0.00841 -0.0744 0.6675 0.0489 -5.500 -0.1888 0.01747 0.00810 -0.0731 0.6658 0.0622 -5.250 -0.1693 0.01713 0.00783 -0.0719 0.6642 0.0799 -5.000 -0.1501 0.01677 0.00758 -0.0707 0.6626 0.1032 -4.500 -0.1142 0.01595 0.00713 -0.0680 0.6595 0.1802 -4.250 -0.0986 0.01543 0.00688 -0.0663 0.6580 0.2411 -4.000 -0.0845 0.01486 0.00664 -0.0643 0.6567 0.3190 -3.750 -0.0728 0.01418 0.00640 -0.0618 0.6553 0.4182 -3.500 -0.0613 0.01353 0.00631 -0.0589 0.6540 0.5414 -3.250 -0.0394 0.01363 0.00690 -0.0569 0.6527 0.6532 -3.000 -0.0138 0.01388 0.00711 -0.0561 0.6515 0.6964 -2.750 0.0109 0.01410 0.00728 -0.0554 0.6502 0.7186 -2.500 0.0353 0.01430 0.00744 -0.0547 0.6488 0.7349 -2.250 0.0598 0.01451 0.00758 -0.0540 0.6474 0.7481 -2.000 0.0845 0.01472 0.00774 -0.0533 0.6460 0.7598 -1.750 0.1107 0.01504 0.00805 -0.0527 0.6446 0.7697 -1.500 0.1351 0.01534 0.00831 -0.0517 0.6433 0.7822 -1.250 0.1606 0.01568 0.00863 -0.0509 0.6419 0.7927 -1.000 0.1861 0.01588 0.00880 -0.0503 0.6404 0.8002 -0.750 0.2129 0.01606 0.00893 -0.0499 0.6390 0.8054 -0.500 0.2382 0.01612 0.00893 -0.0496 0.6378 0.8108 -0.250 0.2639 0.01615 0.00889 -0.0495 0.6368 0.8149 0.000 0.2915 0.01623 0.00894 -0.0496 0.6358 0.8171 0.250 0.3192 0.01632 0.00898 -0.0497 0.6348 0.8195 0.500 0.3447 0.01642 0.00905 -0.0495 0.6334 0.8222 0.750 0.3674 0.01652 0.00918 -0.0489 0.6315 0.8254 1.000 0.3906 0.01662 0.00928 -0.0485 0.6299 0.8288 1.250 0.4145 0.01670 0.00936 -0.0482 0.6280 0.8316 1.500 0.4393 0.01680 0.00948 -0.0479 0.6262 0.8334 1.750 0.4646 0.01690 0.00959 -0.0477 0.6245 0.8352 2.000 0.4905 0.01698 0.00966 -0.0476 0.6229 0.8372 2.250 0.5170 0.01705 0.00972 -0.0477 0.6213 0.8393 2.500 0.5443 0.01709 0.00975 -0.0479 0.6199 0.8415 2.750 0.5728 0.01713 0.00976 -0.0484 0.6185 0.8434 3.000 0.6003 0.01721 0.00983 -0.0487 0.6170 0.8457 3.250 0.6183 0.01745 0.01016 -0.0474 0.6139 0.8484 3.500 0.6394 0.01762 0.01041 -0.0466 0.6111 0.8500 3.750 0.6631 0.01774 0.01056 -0.0461 0.6085 0.8516 4.000 0.6889 0.01779 0.01065 -0.0461 0.6062 0.8533 4.250 0.7165 0.01779 0.01066 -0.0462 0.6041 0.8552 4.500 0.7463 0.01774 0.01061 -0.0468 0.6022 0.8572 4.750 0.7715 0.01781 0.01072 -0.0467 0.5995 0.8593 5.000 0.7858 0.01808 0.01110 -0.0448 0.5948 0.8620 5.250 0.8094 0.01812 0.01118 -0.0444 0.5911 0.8642 5.500 0.8376 0.01800 0.01109 -0.0446 0.5880 0.8658 5.750 0.8702 0.01777 0.01085 -0.0455 0.5853 0.8671 6.000 0.8818 0.01800 0.01122 -0.0430 0.5799 0.8700 6.250 0.9004 0.01801 0.01133 -0.0415 0.5746 0.8729 6.500 0.9295 0.01777 0.01110 -0.0418 0.5707 0.8750 6.750 0.9492 0.01778 0.01118 -0.0407 0.5657 0.8778 7.000 0.9598 0.01795 0.01146 -0.0380 0.5591 0.8814 7.250 0.9860 0.01769 0.01125 -0.0377 0.5542 0.8834 7.500 0.9864 0.01796 0.01166 -0.0332 0.5471 0.8877 7.750 0.9985 0.01798 0.01174 -0.0306 0.5401 0.8918 8.000 1.0008 0.01838 0.01225 -0.0268 0.5317 0.8978 8.250 1.0143 0.01842 0.01236 -0.0246 0.5231 0.9024 8.500 1.0067 0.01935 0.01341 -0.0199 0.5116 0.9107 8.750 1.0080 0.02016 0.01431 -0.0169 0.4987 0.9184 9.000 1.0198 0.02061 0.01480 -0.0153 0.4826 0.9268 9.250 1.0450 0.02043 0.01458 -0.0151 0.4629 0.9339 9.750 1.0817 0.02153 0.01545 -0.0146 0.4085 0.9599 10.250 1.0891 0.02444 0.01807 -0.0119 0.3558 1.0000 10.500 1.0881 0.02611 0.01962 -0.0099 0.3338 1.0000 10.750 1.0870 0.02786 0.02127 -0.0080 0.3125 1.0000 11.000 1.0859 0.02967 0.02298 -0.0062 0.2926 1.0000 11.500 1.0859 0.03330 0.02645 -0.0031 0.2559 1.0000 11.750 1.0880 0.03508 0.02816 -0.0018 0.2396 1.0000 12.000 1.0902 0.03690 0.02992 -0.0006 0.2236 1.0000 12.250 1.0934 0.03870 0.03166 0.0004 0.2088 1.0000 12.500 1.0969 0.04054 0.03345 0.0013 0.1953 1.0000 12.750 1.1013 0.04234 0.03522 0.0021 0.1822 1.0000 13.000 1.1069 0.04409 0.03695 0.0028 0.1702 1.0000 13.250 1.1125 0.04587 0.03872 0.0035 0.1591 1.0000 13.500 1.1176 0.04774 0.04057 0.0041 0.1492 1.0000 13.750 1.1224 0.04968 0.04249 0.0046 0.1392 1.0000 14.000 1.1295 0.05145 0.04427 0.0050 0.1303 1.0000 14.250 1.1342 0.05346 0.04629 0.0054 0.1227 1.0000 14.500 1.1404 0.05538 0.04823 0.0057 0.1147 1.0000 14.750 1.1459 0.05740 0.05026 0.0060 0.1080 1.0000 15.000 1.1513 0.05946 0.05235 0.0062 0.1018 1.0000 15.250 1.1567 0.06155 0.05447 0.0064 0.0963 1.0000 15.500 1.1620 0.06371 0.05667 0.0065 0.0908 1.0000 15.750 1.1657 0.06605 0.05903 0.0065 0.0865 1.0000 16.000 1.1722 0.06815 0.06121 0.0065 0.0819 1.0000 16.250 1.1753 0.07064 0.06373 0.0064 0.0777 1.0000 16.500 1.1797 0.07302 0.06617 0.0062 0.0741 1.0000 16.750 1.1840 0.07547 0.06868 0.0060 0.0699 1.0000 17.000 1.1849 0.07836 0.07160 0.0056 0.0666 1.0000 17.250 1.1902 0.08078 0.07411 0.0052 0.0630 1.0000 17.500 1.1929 0.08354 0.07694 0.0047 0.0597 1.0000 17.750 1.1922 0.08676 0.08017 0.0041 0.0571 1.0000 18.000 1.1970 0.08933 0.08287 0.0035 0.0541 1.0000 18.250 1.1988 0.09235 0.08597 0.0027 0.0516 1.0000 18.500 1.1977 0.09578 0.08945 0.0018 0.0496 1.0000 18.750 1.2000 0.09878 0.09256 0.0009 0.0475 1.0000 19.000 1.2013 0.10195 0.09584 -0.0001 0.0454 1.0000 19.250 1.2002 0.10551 0.09947 -0.0013 0.0434 1.0000