XFOIL Version 6.96 Calculated polar for: RONCZ 1082T VOYAGER TIP OUTER 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.3697 0.10105 0.09611 -0.0588 1.0000 0.0277 -11.250 -0.4269 0.08057 0.07567 -0.0706 1.0000 0.0252 -11.000 -0.4500 0.07368 0.06878 -0.0746 1.0000 0.0250 -10.750 -0.4726 0.06883 0.06392 -0.0762 1.0000 0.0248 -10.500 -0.4894 0.06245 0.05737 -0.0811 0.9713 0.0247 -10.250 -0.4979 0.05667 0.05127 -0.0861 0.9410 0.0246 -10.000 -0.5022 0.05158 0.04575 -0.0895 0.9157 0.0246 -9.750 -0.5054 0.04753 0.04121 -0.0901 0.8919 0.0248 -9.500 -0.5102 0.04382 0.03682 -0.0888 0.8717 0.0253 -9.250 -0.4992 0.04142 0.03416 -0.0883 0.8564 0.0257 -9.000 -0.4858 0.03971 0.03225 -0.0876 0.8429 0.0264 -8.750 -0.4737 0.03777 0.03000 -0.0864 0.8311 0.0269 -8.500 -0.4609 0.03567 0.02751 -0.0849 0.8201 0.0271 -8.250 -0.4455 0.03377 0.02526 -0.0836 0.8101 0.0274 -8.000 -0.4262 0.03194 0.02309 -0.0827 0.8019 0.0280 -7.750 -0.4055 0.03035 0.02122 -0.0819 0.7930 0.0285 -7.500 -0.3814 0.02883 0.01941 -0.0815 0.7862 0.0293 -7.250 -0.3576 0.02753 0.01788 -0.0810 0.7787 0.0301 -7.000 -0.3335 0.02636 0.01654 -0.0806 0.7724 0.0312 -6.750 -0.3116 0.02552 0.01567 -0.0801 0.7668 0.0331 -6.500 -0.2897 0.02474 0.01480 -0.0793 0.7605 0.0354 -6.250 -0.2676 0.02392 0.01382 -0.0785 0.7553 0.0376 -6.000 -0.2480 0.02314 0.01301 -0.0774 0.7502 0.0398 -5.750 -0.2288 0.02248 0.01227 -0.0762 0.7445 0.0430 -5.500 -0.2092 0.02180 0.01153 -0.0750 0.7398 0.0480 -5.250 -0.1890 0.02117 0.01087 -0.0739 0.7357 0.0579 -5.000 -0.1707 0.02054 0.01034 -0.0725 0.7306 0.0784 -4.750 -0.1516 0.01990 0.00989 -0.0713 0.7264 0.1170 -4.250 -0.1198 0.01824 0.00920 -0.0682 0.7197 0.3007 -4.000 -0.1117 0.01737 0.00907 -0.0650 0.7155 0.4439 -3.750 -0.0906 0.01730 0.00983 -0.0622 0.7118 0.6113 -3.500 -0.0632 0.01792 0.01047 -0.0606 0.7085 0.6903 -3.250 -0.0441 0.01820 0.01056 -0.0585 0.7055 0.7278 -3.000 -0.0232 0.01858 0.01080 -0.0567 0.7022 0.7528 -2.750 -0.0046 0.01891 0.01101 -0.0546 0.6986 0.7731 -2.500 0.0188 0.01931 0.01129 -0.0531 0.6955 0.7898 -2.250 0.0437 0.01972 0.01158 -0.0518 0.6928 0.8059 -2.000 0.0711 0.02016 0.01189 -0.0507 0.6905 0.8219 -1.750 0.1072 0.02059 0.01218 -0.0512 0.6884 0.8342 -1.500 0.1345 0.02085 0.01237 -0.0508 0.6851 0.8436 -1.250 0.1510 0.02095 0.01240 -0.0488 0.6817 0.8541 -1.000 0.1838 0.02108 0.01244 -0.0497 0.6790 0.8587 -0.750 0.2095 0.02115 0.01242 -0.0495 0.6766 0.8650 -0.500 0.2316 0.02116 0.01234 -0.0487 0.6745 0.8713 -0.250 0.2638 0.02121 0.01229 -0.0497 0.6727 0.8750 0.000 0.2847 0.02133 0.01238 -0.0488 0.6697 0.8806 0.250 0.2999 0.02144 0.01249 -0.0469 0.6662 0.8866 0.500 0.3277 0.02156 0.01258 -0.0472 0.6635 0.8900 0.750 0.3525 0.02166 0.01264 -0.0471 0.6611 0.8942 1.000 0.3701 0.02170 0.01263 -0.0455 0.6589 0.8998 1.250 0.3999 0.02174 0.01262 -0.0462 0.6570 0.9026 1.500 0.4251 0.02192 0.01280 -0.0462 0.6543 0.9058 1.750 0.4414 0.02222 0.01315 -0.0448 0.6507 0.9105 2.000 0.4529 0.02240 0.01335 -0.0423 0.6474 0.9160 2.250 0.4818 0.02254 0.01349 -0.0429 0.6448 0.9184 2.500 0.5112 0.02263 0.01358 -0.0436 0.6426 0.9209 2.750 0.5404 0.02269 0.01362 -0.0443 0.6407 0.9235 3.000 0.5484 0.02312 0.01414 -0.0414 0.6364 0.9293 3.250 0.5658 0.02350 0.01459 -0.0403 0.6323 0.9330 3.500 0.5924 0.02369 0.01482 -0.0406 0.6292 0.9356 3.750 0.6215 0.02377 0.01493 -0.0413 0.6267 0.9385 4.000 0.6518 0.02378 0.01494 -0.0420 0.6246 0.9414 4.250 0.6556 0.02452 0.01582 -0.0388 0.6185 0.9473 4.500 0.6799 0.02484 0.01622 -0.0390 0.6143 0.9504 4.750 0.7107 0.02489 0.01632 -0.0399 0.6113 0.9533 5.000 0.7449 0.02479 0.01625 -0.0411 0.6090 0.9560 5.250 0.7521 0.02569 0.01730 -0.0390 0.6017 0.9624 5.500 0.7807 0.02584 0.01755 -0.0397 0.5973 0.9655 5.750 0.8169 0.02563 0.01740 -0.0413 0.5942 0.9677 6.000 0.8328 0.02624 0.01814 -0.0403 0.5877 0.9736 6.250 0.8621 0.02639 0.01841 -0.0413 0.5816 0.9774 6.500 0.9038 0.02587 0.01797 -0.0434 0.5780 0.9792 6.750 0.9180 0.02660 0.01887 -0.0426 0.5690 0.9870 7.000 0.9570 0.02604 0.01840 -0.0443 0.5635 0.9896 7.250 0.9746 0.02640 0.01892 -0.0436 0.5544 0.9995 7.500 0.9902 0.02594 0.01851 -0.0411 0.5479 1.0000 7.750 0.9547 0.02674 0.01934 -0.0314 0.5396 1.0000 8.000 0.9797 0.02618 0.01886 -0.0305 0.5320 1.0000 8.250 0.9604 0.02741 0.02015 -0.0245 0.5208 1.0000 8.500 0.9704 0.02770 0.02052 -0.0224 0.5107 1.0000 8.750 0.9908 0.02745 0.02035 -0.0212 0.5003 1.0000 9.000 0.9815 0.02904 0.02201 -0.0179 0.4859 1.0000 9.250 0.9812 0.03034 0.02340 -0.0157 0.4704 1.0000 9.500 0.9707 0.03275 0.02589 -0.0134 0.4507 1.0000 9.750 0.9839 0.03331 0.02649 -0.0123 0.4325 1.0000 10.000 1.0120 0.03250 0.02567 -0.0115 0.4118 1.0000 10.250 1.0323 0.03239 0.02547 -0.0103 0.3846 1.0000 10.500 1.0476 0.03268 0.02561 -0.0089 0.3535 1.0000 10.750 1.0537 0.03384 0.02659 -0.0072 0.3229 1.0000 11.000 1.0553 0.03549 0.02809 -0.0055 0.2942 1.0000 11.250 1.0555 0.03736 0.02983 -0.0040 0.2677 1.0000 11.500 1.0549 0.03937 0.03171 -0.0026 0.2432 1.0000 11.750 1.0550 0.04143 0.03369 -0.0014 0.2205 1.0000 12.000 1.0551 0.04354 0.03570 -0.0003 0.2003 1.0000 12.250 1.0567 0.04563 0.03773 0.0006 0.1811 1.0000 12.500 1.0582 0.04780 0.03984 0.0014 0.1638 1.0000 12.750 1.0605 0.04997 0.04197 0.0020 0.1489 1.0000 13.000 1.0633 0.05215 0.04413 0.0026 0.1356 1.0000 13.250 1.0662 0.05439 0.04635 0.0031 0.1237 1.0000 13.500 1.0690 0.05669 0.04863 0.0034 0.1134 1.0000 13.750 1.0716 0.05907 0.05102 0.0037 0.1041 1.0000 14.000 1.0760 0.06133 0.05334 0.0039 0.0953 1.0000 14.250 1.0784 0.06384 0.05584 0.0041 0.0881 1.0000 14.500 1.0815 0.06635 0.05841 0.0041 0.0808 1.0000 14.750 1.0845 0.06892 0.06102 0.0040 0.0744 1.0000 15.000 1.0859 0.07174 0.06389 0.0038 0.0685 1.0000 15.250 1.0884 0.07449 0.06671 0.0035 0.0629 1.0000 15.500 1.0892 0.07754 0.06983 0.0031 0.0581 1.0000 15.750 1.0905 0.08054 0.07291 0.0026 0.0537 1.0000 16.000 1.0917 0.08364 0.07611 0.0020 0.0498 1.0000 16.250 1.0903 0.08708 0.07955 0.0013 0.0469 1.0000 16.500 1.0927 0.09015 0.08280 0.0007 0.0435 1.0000 16.750 1.0923 0.09363 0.08637 -0.0003 0.0408 1.0000 17.000 1.0909 0.09724 0.08999 -0.0013 0.0388 1.0000 17.250 1.0916 0.10070 0.09366 -0.0023 0.0361 1.0000 17.500 1.0915 0.10428 0.09735 -0.0034 0.0344 1.0000 17.750 1.0890 0.10829 0.10141 -0.0050 0.0327 1.0000 18.000 1.0881 0.11210 0.10536 -0.0064 0.0312 1.0000 18.250 1.0876 0.11592 0.10937 -0.0078 0.0299 1.0000 18.500 1.0860 0.11997 0.11357 -0.0095 0.0287 1.0000 18.750 1.0844 0.12406 0.11778 -0.0113 0.0279 1.0000 19.000 1.0829 0.12813 0.12194 -0.0133 0.0270 1.0000 19.250 1.0836 0.13172 0.12555 -0.0150 0.0263 1.0000