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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.2849 0.09631 0.09061 -0.0910 0.8186 0.0272 -12.500 -0.3027 0.08692 0.08119 -0.0960 0.8129 0.0268 -12.250 -0.3419 0.07417 0.06830 -0.1046 0.8086 0.0260 -12.000 -0.3816 0.06541 0.05931 -0.1100 0.8025 0.0256 -11.750 -0.4102 0.05990 0.05354 -0.1118 0.7960 0.0253 -11.500 -0.4338 0.05558 0.04893 -0.1119 0.7905 0.0252 -11.250 -0.4528 0.05205 0.04514 -0.1108 0.7845 0.0252 -11.000 -0.4666 0.04910 0.04192 -0.1091 0.7789 0.0252 -10.750 -0.4770 0.04643 0.03893 -0.1069 0.7743 0.0253 -10.500 -0.4830 0.04407 0.03629 -0.1044 0.7697 0.0254 -10.250 -0.4864 0.04190 0.03383 -0.1017 0.7650 0.0257 -10.000 -0.4855 0.03995 0.03159 -0.0991 0.7609 0.0260 -9.750 -0.4802 0.03822 0.02953 -0.0967 0.7574 0.0265 -9.500 -0.4721 0.03649 0.02738 -0.0946 0.7541 0.0274 -9.250 -0.4580 0.03509 0.02585 -0.0934 0.7502 0.0283 -9.000 -0.4423 0.03406 0.02472 -0.0923 0.7464 0.0294 -8.750 -0.4232 0.03275 0.02321 -0.0914 0.7431 0.0304 -8.500 -0.4008 0.03138 0.02161 -0.0910 0.7403 0.0314 -8.250 -0.3762 0.03006 0.02004 -0.0907 0.7380 0.0325 -8.000 -0.3563 0.02909 0.01909 -0.0900 0.7352 0.0337 -7.750 -0.3364 0.02823 0.01819 -0.0892 0.7323 0.0352 -7.500 -0.3162 0.02747 0.01728 -0.0883 0.7296 0.0377 -7.250 -0.2990 0.02678 0.01663 -0.0870 0.7271 0.0407 -7.000 -0.2804 0.02611 0.01582 -0.0858 0.7248 0.0440 -6.750 -0.2638 0.02543 0.01515 -0.0844 0.7228 0.0475 -6.500 -0.2465 0.02479 0.01446 -0.0829 0.7209 0.0531 -6.250 -0.2304 0.02427 0.01396 -0.0813 0.7184 0.0615 -6.000 -0.2149 0.02376 0.01353 -0.0797 0.7156 0.0735 -5.750 -0.1984 0.02329 0.01312 -0.0781 0.7130 0.0922 -5.500 -0.1821 0.02280 0.01279 -0.0766 0.7108 0.1188 -5.250 -0.1658 0.02231 0.01249 -0.0750 0.7088 0.1544 -5.000 -0.1502 0.02179 0.01221 -0.0734 0.7070 0.2041 -4.750 -0.1372 0.02118 0.01196 -0.0712 0.7053 0.2750 -4.500 -0.1282 0.02049 0.01174 -0.0684 0.7038 0.3727 -4.250 -0.1199 0.01993 0.01187 -0.0648 0.7022 0.5019 -4.000 -0.0762 0.02102 0.01358 -0.0649 0.7003 0.6414 -3.750 -0.0625 0.02154 0.01404 -0.0620 0.6977 0.6836 -3.500 -0.0539 0.02185 0.01425 -0.0585 0.6951 0.7133 -3.250 -0.0356 0.02235 0.01464 -0.0564 0.6930 0.7348 -3.000 -0.0151 0.02286 0.01503 -0.0546 0.6913 0.7523 -2.750 0.0076 0.02335 0.01540 -0.0531 0.6898 0.7677 -2.500 0.0304 0.02381 0.01574 -0.0516 0.6883 0.7825 -2.250 0.0539 0.02431 0.01613 -0.0501 0.6870 0.7978 -2.000 0.0912 0.02493 0.01662 -0.0508 0.6859 0.8097 -1.750 0.1141 0.02545 0.01710 -0.0497 0.6835 0.8196 -1.500 0.1180 0.02584 0.01749 -0.0458 0.6804 0.8315 -1.250 0.1485 0.02627 0.01786 -0.0463 0.6784 0.8364 -1.000 0.1656 0.02657 0.01810 -0.0447 0.6762 0.8438 -0.750 0.1809 0.02673 0.01820 -0.0428 0.6740 0.8506 -0.500 0.2097 0.02687 0.01827 -0.0433 0.6723 0.8544 -0.250 0.2316 0.02694 0.01826 -0.0425 0.6706 0.8596 0.000 0.2448 0.02697 0.01821 -0.0403 0.6692 0.8659 0.250 0.2652 0.02735 0.01858 -0.0396 0.6669 0.8693 0.500 0.2506 0.02829 0.01961 -0.0334 0.6611 0.8769 0.750 0.2529 0.02865 0.01995 -0.0297 0.6578 0.8830 1.000 0.2784 0.02881 0.02007 -0.0297 0.6557 0.8858 1.250 0.3038 0.02890 0.02011 -0.0297 0.6539 0.8890 1.500 0.3272 0.02893 0.02009 -0.0293 0.6524 0.8925 2.000 0.2954 0.03103 0.02230 -0.0174 0.6396 0.9059 2.250 0.3190 0.03106 0.02230 -0.0170 0.6376 0.9093 2.500 0.3441 0.03099 0.02219 -0.0168 0.6360 0.9125 2.750 0.3748 0.03094 0.02210 -0.0175 0.6348 0.9148 3.750 0.3643 0.03570 0.02702 -0.0054 0.6063 0.9378 4.000 0.3931 0.03569 0.02701 -0.0059 0.6040 0.9407 4.250 0.4241 0.03554 0.02685 -0.0064 0.6025 0.9435 4.500 0.4596 0.03531 0.02663 -0.0077 0.6013 0.9454 5.000 0.4850 0.03749 0.02891 -0.0071 0.5867 0.9557 5.250 0.5201 0.03723 0.02868 -0.0082 0.5853 0.9587 5.750 0.5571 0.03909 0.03067 -0.0093 0.5709 0.9678 6.000 0.5937 0.03872 0.03033 -0.0106 0.5692 0.9710 6.500 0.6360 0.04034 0.03211 -0.0125 0.5546 0.9820 6.750 0.6766 0.03971 0.03155 -0.0142 0.5530 0.9857 7.000 0.6784 0.04153 0.03345 -0.0138 0.5401 1.0000 7.250 0.7023 0.04072 0.03266 -0.0126 0.5380 1.0000 7.500 0.6888 0.04220 0.03415 -0.0090 0.5251 1.0000 7.750 0.7201 0.04140 0.03340 -0.0089 0.5229 1.0000 8.250 0.7503 0.04201 0.03410 -0.0071 0.5077 1.0000 8.500 0.7519 0.04340 0.03553 -0.0056 0.4950 1.0000 9.000 0.7892 0.04372 0.03597 -0.0044 0.4796 1.0000 9.250 0.7984 0.04468 0.03699 -0.0034 0.4681 1.0000 9.500 0.8293 0.04377 0.03615 -0.0033 0.4636 1.0000 9.750 0.8398 0.04467 0.03712 -0.0024 0.4513 1.0000 10.000 0.8582 0.04491 0.03741 -0.0018 0.4411 1.0000 10.250 0.8879 0.04407 0.03663 -0.0016 0.4332 1.0000 10.500 0.9050 0.04441 0.03703 -0.0009 0.4200 1.0000 10.750 0.9268 0.04434 0.03699 -0.0004 0.4070 1.0000 11.000 0.9508 0.04404 0.03669 0.0001 0.3927 1.0000 11.250 0.9733 0.04388 0.03652 0.0007 0.3764 1.0000 11.500 0.9938 0.04391 0.03649 0.0014 0.3579 1.0000 11.750 1.0116 0.04419 0.03668 0.0022 0.3383 1.0000 12.000 1.0236 0.04510 0.03752 0.0030 0.3186 1.0000 12.250 1.0330 0.04629 0.03865 0.0039 0.2989 1.0000 12.500 1.0413 0.04762 0.03991 0.0047 0.2798 1.0000 12.750 1.0486 0.04911 0.04132 0.0055 0.2615 1.0000 13.000 1.0552 0.05070 0.04285 0.0063 0.2447 1.0000 13.250 1.0609 0.05244 0.04455 0.0069 0.2289 1.0000 13.500 1.0662 0.05430 0.04637 0.0075 0.2140 1.0000 13.750 1.0714 0.05621 0.04827 0.0080 0.2002 1.0000 14.000 1.0764 0.05819 0.05024 0.0084 0.1875 1.0000 14.250 1.0815 0.06021 0.05224 0.0088 0.1760 1.0000 14.500 1.0858 0.06232 0.05432 0.0091 0.1653 1.0000 14.750 1.0903 0.06452 0.05655 0.0093 0.1551 1.0000 15.000 1.0954 0.06666 0.05874 0.0094 0.1459 1.0000 15.250 1.0989 0.06898 0.06100 0.0095 0.1381 1.0000 15.500 1.1042 0.07123 0.06336 0.0095 0.1298 1.0000 15.750 1.1082 0.07356 0.06567 0.0095 0.1234 1.0000 16.000 1.1131 0.07592 0.06815 0.0094 0.1166 1.0000 16.250 1.1164 0.07839 0.07057 0.0092 0.1111 1.0000 16.500 1.1215 0.08081 0.07314 0.0090 0.1053 1.0000 16.750 1.1246 0.08341 0.07576 0.0087 0.1004 1.0000 17.000 1.1293 0.08588 0.07831 0.0083 0.0958 1.0000 17.250 1.1323 0.08863 0.08117 0.0078 0.0912 1.0000 17.500 1.1358 0.09122 0.08373 0.0074 0.0876 1.0000 17.750 1.1389 0.09405 0.08674 0.0068 0.0836 1.0000 18.000 1.1406 0.09707 0.08986 0.0060 0.0798 1.0000 18.250 1.1430 0.09990 0.09268 0.0052 0.0767 1.0000 18.500 1.1440 0.10312 0.09608 0.0043 0.0735 1.0000 18.750 1.1434 0.10661 0.09970 0.0031 0.0702 1.0000 19.000 1.1437 0.10991 0.10304 0.0019 0.0674 1.0000 19.250 1.1436 0.11333 0.10655 0.0006 0.0647 1.0000