XFOIL Version 6.96 Calculated polar for: FX 75-VG-166/22 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.4164 0.07837 0.07332 -0.1033 0.7682 0.0156 -13.250 -0.4508 0.06868 0.06346 -0.1097 0.7679 0.0155 -13.000 -0.4705 0.06329 0.05794 -0.1124 0.7673 0.0154 -12.750 -0.4986 0.05778 0.05220 -0.1138 0.7667 0.0154 -12.500 -0.5203 0.05362 0.04783 -0.1136 0.7659 0.0154 -12.250 -0.5389 0.05003 0.04404 -0.1124 0.7650 0.0154 -12.000 -0.5502 0.04727 0.04108 -0.1107 0.7641 0.0153 -11.750 -0.5703 0.04371 0.03717 -0.1077 0.7629 0.0155 -11.500 -0.5774 0.04131 0.03451 -0.1052 0.7617 0.0156 -11.250 -0.5808 0.03911 0.03201 -0.1027 0.7605 0.0157 -11.000 -0.5786 0.03727 0.03002 -0.1005 0.7596 0.0160 -10.750 -0.5715 0.03622 0.02891 -0.0988 0.7586 0.0165 -10.500 -0.5633 0.03445 0.02691 -0.0969 0.7575 0.0165 -10.250 -0.5542 0.03368 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0.02274 0.01627 -0.0382 0.7037 0.8066 -0.500 0.1498 0.02285 0.01636 -0.0376 0.7020 0.8086 -0.250 0.1742 0.02290 0.01637 -0.0371 0.7005 0.8114 0.000 0.1987 0.02284 0.01627 -0.0367 0.6992 0.8145 0.250 0.2233 0.02268 0.01604 -0.0366 0.6980 0.8184 0.500 0.2498 0.02251 0.01582 -0.0366 0.6970 0.8208 0.750 0.2556 0.02304 0.01643 -0.0335 0.6896 0.8228 1.000 0.2788 0.02305 0.01643 -0.0330 0.6876 0.8246 1.250 0.3034 0.02301 0.01638 -0.0327 0.6861 0.8265 1.500 0.3296 0.02290 0.01625 -0.0326 0.6849 0.8287 1.750 0.3569 0.02275 0.01607 -0.0328 0.6838 0.8309 2.250 0.3830 0.02331 0.01671 -0.0292 0.6736 0.8362 2.500 0.4109 0.02307 0.01647 -0.0293 0.6718 0.8370 2.750 0.4399 0.02282 0.01622 -0.0296 0.6705 0.8379 3.000 0.4687 0.02261 0.01603 -0.0299 0.6695 0.8388 3.500 0.4914 0.02331 0.01682 -0.0259 0.6578 0.8422 3.750 0.5219 0.02298 0.01651 -0.0264 0.6562 0.8431 4.000 0.5541 0.02256 0.01612 -0.0271 0.6550 0.8442 4.250 0.5864 0.02214 0.01573 -0.0279 0.6540 0.8454 4.750 0.6119 0.02267 0.01635 -0.0244 0.6409 0.8486 5.000 0.6441 0.02220 0.01594 -0.0251 0.6397 0.8493 5.500 0.6629 0.02230 0.01616 -0.0194 0.6260 0.8522 6.000 0.6980 0.02188 0.01585 -0.0163 0.6110 0.8548 6.250 0.7022 0.02243 0.01644 -0.0134 0.5986 0.8561 6.500 0.7452 0.02121 0.01526 -0.0150 0.5938 0.8564 6.750 0.7462 0.02211 0.01621 -0.0119 0.5799 0.8577 7.000 0.7588 0.02251 0.01666 -0.0103 0.5677 0.8587 7.250 0.7854 0.02219 0.01639 -0.0101 0.5573 0.8594 7.500 0.8230 0.02130 0.01552 -0.0110 0.5452 0.8598 7.750 0.8574 0.02057 0.01479 -0.0114 0.5273 0.8602 8.000 0.8877 0.01999 0.01411 -0.0113 0.4979 0.8608 8.250 0.9033 0.02008 0.01392 -0.0093 0.4533 0.8620 8.500 0.9053 0.02094 0.01455 -0.0061 0.4139 0.8631 8.750 0.9048 0.02204 0.01545 -0.0030 0.3781 0.8640 9.250 0.8929 0.02489 0.01781 0.0040 0.2982 0.8655 9.500 0.8891 0.02636 0.01907 0.0070 0.2594 0.8662 9.750 0.8890 0.02775 0.02028 0.0094 0.2271 0.8668 10.000 0.8904 0.02915 0.02152 0.0115 0.1978 0.8673 10.250 0.8974 0.03033 0.02262 0.0129 0.1757 0.8678 10.500 0.9037 0.03162 0.02382 0.0142 0.1551 0.8683 10.750 0.9125 0.03282 0.02496 0.0153 0.1374 0.8687 11.000 0.9219 0.03406 0.02614 0.0162 0.1192 0.8690 11.250 0.9319 0.03531 0.02736 0.0169 0.1050 0.8694 11.500 0.9415 0.03661 0.02862 0.0177 0.0892 0.8698 11.750 0.9490 0.03810 0.03001 0.0185 0.0717 0.8701 12.000 0.9576 0.03957 0.03144 0.0193 0.0595 0.8704 12.250 0.9663 0.04108 0.03292 0.0199 0.0497 0.8708 12.500 0.9748 0.04264 0.03447 0.0205 0.0429 0.8713 12.750 0.9834 0.04424 0.03609 0.0210 0.0378 0.8717 13.000 0.9924 0.04583 0.03773 0.0214 0.0348 0.8723 13.250 1.0001 0.04756 0.03952 0.0218 0.0321 0.8727 13.500 1.0084 0.04929 0.04135 0.0222 0.0304 0.8730 13.750 1.0152 0.05120 0.04329 0.0224 0.0278 0.8732 14.000 1.0218 0.05319 0.04535 0.0226 0.0267 0.8735 14.250 1.0289 0.05517 0.04745 0.0228 0.0257 0.8740 14.500 1.0351 0.05730 0.04967 0.0228 0.0246 0.8745 14.750 1.0409 0.05950 0.05196 0.0228 0.0234 0.8753 15.000 1.0453 0.06188 0.05441 0.0227 0.0228 0.8757 15.250 1.0479 0.06452 0.05710 0.0226 0.0221 0.8760 15.500 1.0536 0.06687 0.05958 0.0223 0.0214 0.8761 15.750 1.0590 0.06932 0.06215 0.0220 0.0209 0.8762 16.000 1.0639 0.07186 0.06480 0.0216 0.0201 0.8763 16.250 1.0688 0.07445 0.06749 0.0210 0.0195 0.8764 16.500 1.0714 0.07739 0.07050 0.0202 0.0185 0.8765 16.750 1.0744 0.08027 0.07346 0.0196 0.0182 0.8766 17.000 1.0773 0.08314 0.07639 0.0189 0.0179 0.8767 17.250 1.0806 0.08611 0.07950 0.0182 0.0174 0.8768 17.500 1.0844 0.08900 0.08251 0.0174 0.0173 0.8769 17.750 1.0864 0.09223 0.08592 0.0163 0.0169 0.8771 18.000 1.0876 0.09562 0.08945 0.0152 0.0165 0.8772 18.250 1.0887 0.09907 0.09305 0.0139 0.0163 0.8773 18.500 1.0885 0.10279 0.09692 0.0125 0.0159 0.8774 18.750 1.0882 0.10655 0.10083 0.0109 0.0158 0.8775 19.000 1.0855 0.11077 0.10520 0.0090 0.0155 0.8776 19.250 1.0825 0.11510 0.10967 0.0069 0.0153 0.8777