XFOIL Version 6.96 Calculated polar for: WORTMANN FX 3 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.4560 0.08915 0.08422 -0.1410 0.8350 0.0170 -16.000 -0.4944 0.07879 0.07359 -0.1469 0.8352 0.0168 -15.750 -0.5181 0.07197 0.06654 -0.1504 0.8353 0.0168 -15.500 -0.5347 0.06672 0.06107 -0.1526 0.8353 0.0170 -15.250 -0.5468 0.06243 0.05656 -0.1540 0.8354 0.0172 -15.000 -0.5551 0.05884 0.05276 -0.1548 0.8355 0.0174 -14.750 -0.5602 0.05576 0.04946 -0.1552 0.8356 0.0177 -14.500 -0.5620 0.05312 0.04660 -0.1554 0.8356 0.0181 -14.250 -0.5607 0.05085 0.04409 -0.1553 0.8357 0.0184 -14.000 -0.5574 0.04889 0.04199 -0.1551 0.8358 0.0189 -13.750 -0.5519 0.04734 0.04038 -0.1550 0.8358 0.0195 -13.500 -0.5445 0.04606 0.03903 -0.1548 0.8359 0.0201 -13.250 -0.5358 0.04491 0.03780 -0.1546 0.8359 0.0208 -13.000 -0.5260 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0.7187 1.750 0.2407 0.04040 0.03362 -0.0636 0.7478 0.7204 2.000 0.2767 0.04028 0.03348 -0.0663 0.7461 0.7217 2.250 0.3079 0.04010 0.03330 -0.0673 0.7448 0.7222 2.750 0.3509 0.04004 0.03329 -0.0668 0.7348 0.7232 3.000 0.3821 0.03982 0.03309 -0.0679 0.7331 0.7238 3.500 0.4265 0.03982 0.03314 -0.0677 0.7224 0.7251 3.750 0.4587 0.03956 0.03292 -0.0690 0.7206 0.7257 4.250 0.5064 0.03961 0.03305 -0.0696 0.7093 0.7268 4.500 0.5402 0.03929 0.03278 -0.0713 0.7074 0.7270 5.000 0.5898 0.03937 0.03298 -0.0721 0.6958 0.7281 5.250 0.6232 0.03903 0.03269 -0.0737 0.6935 0.7284 5.750 0.6758 0.03904 0.03284 -0.0751 0.6814 0.7287 6.000 0.7094 0.03859 0.03246 -0.0766 0.6784 0.7289 6.500 0.7636 0.03839 0.03243 -0.0779 0.6648 0.7291 6.750 0.7952 0.03791 0.03201 -0.0789 0.6576 0.7292 7.000 0.8322 0.03673 0.03087 -0.0803 0.6424 0.7294 7.250 0.8742 0.03525 0.02938 -0.0823 0.6216 0.7299 7.500 0.9173 0.03399 0.02814 -0.0847 0.6060 0.7303 7.750 0.9624 0.03262 0.02675 -0.0873 0.5843 0.7304 8.000 1.0015 0.03169 0.02574 -0.0891 0.5558 0.7305 8.250 1.0309 0.03130 0.02513 -0.0895 0.5111 0.7306 8.500 1.0430 0.03198 0.02548 -0.0877 0.4548 0.7306 8.750 1.0453 0.03336 0.02651 -0.0847 0.3959 0.7306 9.000 1.0450 0.03503 0.02782 -0.0816 0.3357 0.7306 9.250 1.0453 0.03678 0.02923 -0.0788 0.2764 0.7306 9.500 1.0470 0.03854 0.03067 -0.0763 0.2215 0.7306 9.750 1.0522 0.04015 0.03200 -0.0743 0.1756 0.7305 10.000 1.0605 0.04160 0.03327 -0.0728 0.1409 0.7306 10.250 1.0714 0.04290 0.03445 -0.0716 0.1177 0.7306 10.500 1.0839 0.04412 0.03561 -0.0707 0.1015 0.7306 10.750 1.0968 0.04532 0.03678 -0.0698 0.0877 0.7306 11.000 1.1101 0.04650 0.03795 -0.0690 0.0755 0.7306 11.250 1.1231 0.04773 0.03916 -0.0681 0.0634 0.7306 11.500 1.1347 0.04909 0.04051 -0.0672 0.0508 0.7306 11.750 1.1459 0.05050 0.04190 -0.0662 0.0401 0.7307 12.000 1.1562 0.05200 0.04338 -0.0652 0.0332 0.7309 12.250 1.1663 0.05353 0.04494 -0.0641 0.0290 0.7311 12.500 1.1755 0.05518 0.04663 -0.0631 0.0264 0.7313 12.750 1.1859 0.05675 0.04830 -0.0622 0.0245 0.7313 13.000 1.1950 0.05847 0.05010 -0.0612 0.0230 0.7313 13.250 1.2022 0.06039 0.05210 -0.0602 0.0217 0.7313 13.500 1.2068 0.06258 0.05438 -0.0590 0.0206 0.7312 13.750 1.2152 0.06444 0.05637 -0.0582 0.0198 0.7312 14.000 1.2230 0.06638 0.05843 -0.0575 0.0189 0.7312 14.250 1.2296 0.06847 0.06063 -0.0567 0.0181 0.7312 14.500 1.2356 0.07065 0.06291 -0.0560 0.0174 0.7312 14.750 1.2403 0.07300 0.06536 -0.0553 0.0169 0.7312 15.000 1.2434 0.07555 0.06799 -0.0546 0.0164 0.7312 15.250 1.2442 0.07831 0.07083 -0.0538 0.0159 0.7312 15.500 1.2491 0.08070 0.07336 -0.0533 0.0156 0.7312 15.750 1.2546 0.08308 0.07588 -0.0529 0.0152 0.7312 16.000 1.2592 0.08558 0.07853 -0.0526 0.0148 0.7312 16.250 1.2634 0.08816 0.08124 -0.0524 0.0143 0.7312 16.500 1.2668 0.09086 0.08407 -0.0524 0.0139 0.7312 16.750 1.2696 0.09367 0.08700 -0.0524 0.0135 0.7312 17.000 1.2718 0.09657 0.09001 -0.0526 0.0132 0.7312 17.250 1.2733 0.09959 0.09313 -0.0529 0.0129 0.7312 17.500 1.2744 0.10267 0.09630 -0.0533 0.0126 0.7312 17.750 1.2753 0.10577 0.09949 -0.0537 0.0124 0.7313 18.000 1.2756 0.10889 0.10272 -0.0541 0.0122 0.7313 18.250 1.2754 0.11238 0.10640 -0.0550 0.0121 0.7313 18.500 1.2736 0.11618 0.11040 -0.0561 0.0119 0.7313 18.750 1.2708 0.12020 0.11462 -0.0575 0.0117 0.7313 19.000 1.2667 0.12448 0.11910 -0.0591 0.0116 0.7313 19.250 1.2615 0.12909 0.12391 -0.0612 0.0114 0.7313