XFOIL Version 6.96 Calculated polar for: DF 101 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.6322 0.04214 0.03775 -0.0429 1.0000 0.0326 -7.500 -0.6383 0.03822 0.03352 -0.0397 1.0000 0.0310 -7.250 -0.6474 0.03242 0.02671 -0.0353 1.0000 0.0276 -7.000 -0.6377 0.03019 0.02407 -0.0328 1.0000 0.0272 -6.750 -0.6259 0.02791 0.02152 -0.0307 1.0000 0.0275 -6.500 -0.5964 0.02627 0.01978 -0.0322 0.9969 0.0295 -6.250 -0.5617 0.02445 0.01765 -0.0340 0.9931 0.0310 -6.000 -0.5284 0.02251 0.01540 -0.0351 0.9887 0.0320 -5.750 -0.4917 0.02108 0.01372 -0.0368 0.9848 0.0338 -5.500 -0.4593 0.01920 0.01175 -0.0380 0.9808 0.0365 -5.250 -0.4254 0.01835 0.01088 -0.0395 0.9752 0.0423 -5.000 -0.3892 0.01704 0.00955 -0.0414 0.9713 0.0489 -4.750 -0.3576 0.01619 0.00868 -0.0423 0.9651 0.0602 -4.500 -0.3233 0.01509 0.00776 -0.0439 0.9599 0.0954 -4.250 -0.2843 0.01425 0.00745 -0.0466 0.9564 0.2125 -4.000 -0.2538 0.01412 0.00731 -0.0472 0.9485 0.2451 -3.750 -0.2135 0.01392 0.00710 -0.0498 0.9443 0.2732 -3.500 -0.1696 0.01374 0.00693 -0.0531 0.9416 0.3079 -3.250 -0.1414 0.01355 0.00680 -0.0532 0.9328 0.3364 -3.000 -0.1005 0.01321 0.00653 -0.0557 0.9291 0.3638 -2.750 -0.0680 0.01290 0.00628 -0.0566 0.9223 0.3894 -2.500 -0.0341 0.01252 0.00602 -0.0577 0.9161 0.4208 -2.250 0.0031 0.01207 0.00573 -0.0593 0.9122 0.4637 -2.000 0.0264 0.01172 0.00560 -0.0582 0.9018 0.5159 -1.750 0.0552 0.01123 0.00543 -0.0579 0.8954 0.5967 -1.500 0.0781 0.01077 0.00534 -0.0563 0.8861 0.6912 -1.250 0.1058 0.01037 0.00532 -0.0551 0.8786 0.8017 -1.000 0.1512 0.01025 0.00533 -0.0574 0.8721 0.8955 -0.750 0.1991 0.01019 0.00520 -0.0605 0.8659 0.9395 -0.500 0.2507 0.01014 0.00507 -0.0648 0.8570 0.9631 -0.250 0.3034 0.01002 0.00486 -0.0694 0.8472 0.9809 0.000 0.3587 0.00981 0.00453 -0.0746 0.8361 0.9952 0.250 0.3921 0.00966 0.00428 -0.0756 0.8218 1.0000 0.500 0.4132 0.00959 0.00412 -0.0741 0.8069 1.0000 0.750 0.4349 0.00955 0.00400 -0.0727 0.7922 1.0000 1.000 0.4569 0.00954 0.00390 -0.0713 0.7775 1.0000 1.250 0.4792 0.00955 0.00384 -0.0700 0.7626 1.0000 1.500 0.5017 0.00958 0.00380 -0.0688 0.7473 1.0000 1.750 0.5243 0.00963 0.00377 -0.0675 0.7317 1.0000 2.000 0.5470 0.00970 0.00377 -0.0663 0.7158 1.0000 2.250 0.5697 0.00977 0.00379 -0.0651 0.6994 1.0000 2.500 0.5925 0.00987 0.00382 -0.0639 0.6828 1.0000 2.750 0.6152 0.00998 0.00386 -0.0627 0.6656 1.0000 3.000 0.6380 0.01011 0.00392 -0.0615 0.6482 1.0000 3.250 0.6604 0.01025 0.00401 -0.0603 0.6296 1.0000 3.500 0.6826 0.01040 0.00411 -0.0590 0.6097 1.0000 3.750 0.7048 0.01058 0.00420 -0.0577 0.5893 1.0000 4.000 0.7265 0.01075 0.00435 -0.0563 0.5666 1.0000 4.250 0.7479 0.01097 0.00448 -0.0549 0.5429 1.0000 4.500 0.7687 0.01121 0.00464 -0.0534 0.5161 1.0000 4.750 0.7890 0.01149 0.00482 -0.0519 0.4869 1.0000 5.000 0.8086 0.01182 0.00505 -0.0502 0.4555 1.0000 5.250 0.8278 0.01220 0.00530 -0.0486 0.4215 1.0000 5.500 0.8467 0.01265 0.00561 -0.0469 0.3890 1.0000 5.750 0.8656 0.01314 0.00596 -0.0453 0.3598 1.0000 6.000 0.8847 0.01366 0.00636 -0.0438 0.3347 1.0000 6.250 0.9043 0.01419 0.00679 -0.0424 0.3132 1.0000 6.500 0.9239 0.01475 0.00724 -0.0410 0.2952 1.0000 6.750 0.9444 0.01526 0.00771 -0.0397 0.2788 1.0000 7.000 0.9648 0.01579 0.00820 -0.0385 0.2643 1.0000 7.250 0.9851 0.01635 0.00873 -0.0373 0.2510 1.0000 7.500 1.0056 0.01686 0.00925 -0.0362 0.2383 1.0000 7.750 1.0261 0.01735 0.00978 -0.0350 0.2262 1.0000 8.000 1.0461 0.01787 0.01033 -0.0338 0.2143 1.0000 8.250 1.0652 0.01837 0.01084 -0.0325 0.2017 1.0000 8.500 1.0833 0.01881 0.01133 -0.0310 0.1883 1.0000 8.750 1.1009 0.01924 0.01178 -0.0296 0.1746 1.0000 9.000 1.1183 0.01974 0.01231 -0.0281 0.1630 1.0000 9.250 1.1347 0.02027 0.01285 -0.0265 0.1513 1.0000 9.500 1.1508 0.02078 0.01341 -0.0248 0.1388 1.0000 9.750 1.1658 0.02131 0.01402 -0.0230 0.1257 1.0000 10.000 1.1789 0.02191 0.01467 -0.0208 0.1100 1.0000 10.250 1.1879 0.02280 0.01550 -0.0183 0.0877 1.0000 10.500 1.1887 0.02435 0.01687 -0.0149 0.0634 1.0000 10.750 1.1885 0.02605 0.01851 -0.0116 0.0506 1.0000 11.000 1.1916 0.02756 0.02006 -0.0090 0.0445 1.0000 11.250 1.1909 0.02941 0.02196 -0.0062 0.0407 1.0000 11.500 1.1949 0.03102 0.02368 -0.0040 0.0379 1.0000 11.750 1.1969 0.03285 0.02558 -0.0021 0.0358 1.0000 12.000 1.1957 0.03508 0.02786 -0.0001 0.0342 1.0000 12.250 1.1968 0.03741 0.03026 0.0016 0.0328 1.0000 12.500 1.2026 0.03929 0.03229 0.0029 0.0319 1.0000 12.750 1.2074 0.04133 0.03448 0.0040 0.0307 1.0000 13.000 1.2113 0.04349 0.03675 0.0050 0.0295 1.0000 13.250 1.2137 0.04577 0.03912 0.0057 0.0281 1.0000 13.500 1.2173 0.04817 0.04161 0.0064 0.0274 1.0000 13.750 1.2210 0.05078 0.04431 0.0072 0.0268 1.0000 14.000 1.2246 0.05388 0.04752 0.0080 0.0261 1.0000 14.250 1.2240 0.05767 0.05152 0.0086 0.0256 1.0000 14.500 1.2183 0.06114 0.05522 0.0084 0.0254 1.0000 14.750 1.2111 0.06497 0.05927 0.0079 0.0251 1.0000 15.000 1.2017 0.06918 0.06370 0.0069 0.0249 1.0000 15.250 1.1914 0.07376 0.06850 0.0055 0.0247 1.0000 15.500 1.1776 0.07904 0.07401 0.0033 0.0244 1.0000 15.750 1.1630 0.08480 0.08000 0.0007 0.0242 1.0000 16.000 1.1469 0.09116 0.08655 -0.0024 0.0243 1.0000 16.250 1.1285 0.09829 0.09388 -0.0064 0.0242 1.0000 16.500 1.1081 0.10625 0.10205 -0.0110 0.0244 1.0000 16.750 1.0862 0.11497 0.11095 -0.0164 0.0247 1.0000 17.000 1.0612 0.12491 0.12107 -0.0226 0.0250 1.0000 17.250 1.0346 0.13578 0.13209 -0.0295 0.0254 1.0000 17.500 0.7099 0.17865 0.17561 -0.0535 0.0426 1.0000