XFOIL Version 6.96 Calculated polar for: WORTMANN FX 049-915 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.1851 0.09115 0.08649 -0.0636 0.4764 0.0099 -10.500 -0.2444 0.07667 0.07215 -0.0694 0.4773 0.0103 -10.250 -0.5385 0.03188 0.02666 -0.0812 0.4822 0.0097 -10.000 -0.5373 0.02824 0.02263 -0.0789 0.4813 0.0098 -9.750 -0.5269 0.02606 0.02015 -0.0771 0.4803 0.0099 -9.500 -0.5116 0.02448 0.01831 -0.0757 0.4793 0.0101 -9.250 -0.4950 0.02313 0.01673 -0.0743 0.4782 0.0103 -9.000 -0.4775 0.02200 0.01543 -0.0729 0.4771 0.0106 -8.750 -0.4572 0.02118 0.01447 -0.0718 0.4759 0.0109 -8.500 -0.4354 0.02044 0.01362 -0.0709 0.4751 0.0112 -8.250 -0.4132 0.01971 0.01278 -0.0700 0.4743 0.0116 -8.000 -0.3903 0.01906 0.01202 -0.0692 0.4734 0.0122 -7.750 -0.3671 0.01841 0.01123 -0.0684 0.4724 0.0126 -7.500 -0.3436 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0.01336 0.00505 -0.0588 0.4547 0.0549 -2.500 0.1766 0.01342 0.00506 -0.0587 0.4540 0.0566 -2.250 0.2027 0.01323 0.00485 -0.0583 0.4532 0.0584 -2.000 0.2284 0.01300 0.00461 -0.0578 0.4524 0.0599 -1.750 0.2546 0.01286 0.00445 -0.0574 0.4516 0.0610 -1.500 0.2810 0.01274 0.00430 -0.0571 0.4507 0.0621 -1.250 0.3073 0.01263 0.00417 -0.0567 0.4498 0.0635 -1.000 0.3338 0.01254 0.00407 -0.0564 0.4491 0.0652 -0.750 0.3604 0.01249 0.00399 -0.0561 0.4484 0.0671 -0.500 0.3869 0.01243 0.00390 -0.0558 0.4477 0.0685 -0.250 0.4135 0.01239 0.00384 -0.0555 0.4470 0.0697 0.000 0.4402 0.01237 0.00380 -0.0552 0.4463 0.0704 0.250 0.4665 0.01233 0.00374 -0.0549 0.4457 0.0716 0.500 0.4929 0.01231 0.00372 -0.0547 0.4449 0.0733 0.750 0.5195 0.01232 0.00373 -0.0544 0.4443 0.0748 1.000 0.5462 0.01231 0.00374 -0.0542 0.4438 0.0766 1.250 0.5730 0.01231 0.00376 -0.0540 0.4433 0.0783 1.500 0.5997 0.01232 0.00379 -0.0538 0.4426 0.0803 1.750 0.6263 0.01233 0.00383 -0.0536 0.4419 0.0831 2.000 0.6529 0.01234 0.00388 -0.0534 0.4410 0.0875 2.250 0.6795 0.01236 0.00394 -0.0532 0.4403 0.0958 2.500 0.6991 0.01174 0.00404 -0.0520 0.4396 0.3846 3.000 0.8484 0.01067 0.00455 -0.0728 0.4379 0.9917 3.250 0.8899 0.01079 0.00466 -0.0759 0.4371 0.9973 3.500 0.9280 0.01089 0.00475 -0.0783 0.4364 1.0000 3.750 0.9524 0.01100 0.00486 -0.0778 0.4356 1.0000 4.000 0.9768 0.01110 0.00497 -0.0772 0.4348 1.0000 4.250 1.0013 0.01121 0.00507 -0.0767 0.4340 1.0000 4.500 1.0258 0.01133 0.00521 -0.0762 0.4333 1.0000 4.750 1.0504 0.01146 0.00535 -0.0757 0.4327 1.0000 5.000 1.0750 0.01160 0.00549 -0.0752 0.4321 1.0000 5.250 1.0997 0.01174 0.00566 -0.0747 0.4314 1.0000 5.500 1.1245 0.01190 0.00582 -0.0743 0.4306 1.0000 5.750 1.1492 0.01208 0.00601 -0.0739 0.4298 1.0000 6.000 1.1737 0.01226 0.00623 -0.0735 0.4290 1.0000 6.250 1.1978 0.01243 0.00646 -0.0729 0.4283 1.0000 6.500 1.2218 0.01260 0.00670 -0.0724 0.4275 1.0000 6.750 1.2456 0.01276 0.00693 -0.0719 0.4265 1.0000 7.000 1.2695 0.01290 0.00714 -0.0713 0.4251 1.0000 7.250 1.2934 0.01296 0.00726 -0.0708 0.4230 1.0000 7.500 1.3177 0.01299 0.00735 -0.0703 0.4207 1.0000 7.750 1.3421 0.01299 0.00738 -0.0698 0.4185 1.0000 8.000 1.3666 0.01300 0.00741 -0.0694 0.4163 1.0000 8.250 1.3897 0.01298 0.00746 -0.0687 0.4121 1.0000 8.500 1.4126 0.01293 0.00750 -0.0679 0.4060 1.0000 8.750 1.4361 0.01289 0.00747 -0.0673 0.4012 1.0000 9.000 1.4590 0.01299 0.00766 -0.0666 0.3959 1.0000 9.250 1.4809 0.01299 0.00769 -0.0658 0.3861 1.0000 9.500 1.5018 0.01310 0.00784 -0.0648 0.3715 1.0000 9.750 1.5172 0.01345 0.00809 -0.0630 0.3454 1.0000 10.000 1.5162 0.01460 0.00901 -0.0587 0.3036 1.0000 10.250 1.5025 0.01637 0.01057 -0.0528 0.2649 1.0000 10.500 1.4831 0.01799 0.01210 -0.0460 0.2398 1.0000 10.750 1.4649 0.02001 0.01410 -0.0409 0.2213 1.0000 11.250 1.4120 0.02986 0.02409 -0.0392 0.1933 1.0000 11.500 1.3798 0.03569 0.02995 -0.0384 0.1815 1.0000 11.750 1.3509 0.04083 0.03509 -0.0373 0.1703 1.0000 12.000 1.3234 0.04577 0.04001 -0.0363 0.1568 1.0000 12.250 1.3004 0.05030 0.04449 -0.0354 0.1422 1.0000 12.500 1.2842 0.05441 0.04857 -0.0348 0.1284 1.0000 12.750 1.2700 0.05850 0.05259 -0.0344 0.1131 1.0000 13.000 1.2603 0.06220 0.05622 -0.0342 0.0991 1.0000 13.250 1.2513 0.06589 0.05984 -0.0340 0.0849 1.0000 13.500 1.2468 0.06914 0.06304 -0.0339 0.0736 1.0000 13.750 1.2435 0.07227 0.06612 -0.0338 0.0590 1.0000 14.000 1.2233 0.07743 0.07105 -0.0338 0.0287 1.0000 14.250 1.2232 0.08030 0.07391 -0.0338 0.0231 1.0000 14.500 1.2264 0.08284 0.07649 -0.0339 0.0195 1.0000 14.750 1.2288 0.08551 0.07923 -0.0340 0.0178 1.0000 15.000 1.2311 0.08818 0.08193 -0.0341 0.0161 1.0000 15.250 1.2346 0.09072 0.08451 -0.0343 0.0146 1.0000 15.500 1.2385 0.09324 0.08709 -0.0344 0.0136 1.0000 15.750 1.2410 0.09596 0.08986 -0.0347 0.0128 1.0000 16.000 1.2438 0.09865 0.09260 -0.0350 0.0122 1.0000