XFOIL Version 6.96 Calculated polar for: WORTMANN FX 71-120 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.4531 0.06863 0.06478 -0.0419 1.0000 0.0250 -19.500 -1.4835 0.06090 0.05689 -0.0462 1.0000 0.0253 -19.250 -1.5065 0.05451 0.05036 -0.0496 1.0000 0.0257 -19.000 -1.5235 0.04920 0.04492 -0.0522 1.0000 0.0263 -18.750 -1.5340 0.04495 0.04055 -0.0540 1.0000 0.0267 -18.500 -1.5424 0.04119 0.03669 -0.0553 1.0000 0.0276 -18.250 -1.5470 0.03805 0.03346 -0.0561 1.0000 0.0284 -18.000 -1.5522 0.03506 0.03040 -0.0564 1.0000 0.0301 -17.750 -1.5514 0.03282 0.02814 -0.0563 1.0000 0.0324 -17.500 -1.5382 0.03179 0.02719 -0.0560 1.0000 0.0364 -17.250 -1.5247 0.03084 0.02622 -0.0556 1.0000 0.0391 -17.000 -1.5167 0.02949 0.02479 -0.0550 1.0000 0.0402 -16.750 -1.5019 0.02872 0.02400 -0.0544 1.0000 0.0413 -16.500 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0.01189 0.00592 -0.0064 0.9897 0.0550 -7.000 -0.7711 0.01162 0.00564 -0.0070 0.9869 0.0552 -6.750 -0.7390 0.01135 0.00537 -0.0078 0.9844 0.0553 -6.250 -0.6797 0.01085 0.00486 -0.0084 0.9746 0.0556 -6.000 -0.6496 0.01061 0.00461 -0.0087 0.9681 0.0557 -5.750 -0.6184 0.01038 0.00438 -0.0092 0.9627 0.0559 -5.500 -0.5843 0.01014 0.00415 -0.0104 0.9587 0.0560 -5.250 -0.5502 0.00992 0.00393 -0.0116 0.9527 0.0562 -5.000 -0.5134 0.00969 0.00370 -0.0133 0.9434 0.0563 -4.750 -0.4791 0.00950 0.00348 -0.0144 0.9256 0.0565 -4.500 -0.4506 0.00938 0.00328 -0.0142 0.8950 0.0566 -4.250 -0.4252 0.00929 0.00309 -0.0134 0.8631 0.0569 -3.750 -0.3752 0.00914 0.00276 -0.0116 0.8072 0.0577 -3.500 -0.3502 0.00908 0.00262 -0.0107 0.7784 0.0582 -3.250 -0.3250 0.00904 0.00249 -0.0099 0.7473 0.0589 -3.000 -0.3002 0.00904 0.00237 -0.0090 0.7084 0.0597 -2.750 -0.2762 0.00910 0.00226 -0.0079 0.6528 0.0603 -2.500 -0.2517 0.00919 0.00217 -0.0070 0.5985 0.0609 -2.250 -0.2270 0.00929 0.00209 -0.0062 0.5405 0.0616 -2.000 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0.0089 0.0596 0.7071 3.250 0.3251 0.00904 0.00249 0.0099 0.0589 0.7464 3.500 0.3501 0.00908 0.00262 0.0107 0.0583 0.7797 3.750 0.3753 0.00914 0.00276 0.0116 0.0578 0.8067 4.000 0.4004 0.00921 0.00291 0.0124 0.0573 0.8353 4.250 0.4251 0.00929 0.00309 0.0134 0.0569 0.8650 4.500 0.4506 0.00937 0.00328 0.0143 0.0566 0.8996 4.750 0.4794 0.00950 0.00348 0.0144 0.0565 0.9262 5.000 0.5135 0.00969 0.00370 0.0133 0.0563 0.9436 5.250 0.5502 0.00992 0.00393 0.0116 0.0562 0.9527 5.500 0.5843 0.01014 0.00415 0.0104 0.0560 0.9587 5.750 0.6185 0.01037 0.00438 0.0092 0.0559 0.9627 6.000 0.6497 0.01061 0.00461 0.0087 0.0557 0.9680 6.250 0.6797 0.01085 0.00486 0.0083 0.0556 0.9746 6.750 0.7390 0.01136 0.00537 0.0078 0.0553 0.9844 7.000 0.7712 0.01162 0.00564 0.0070 0.0552 0.9869 7.250 0.8019 0.01189 0.00592 0.0064 0.0550 0.9897 7.500 0.8314 0.01218 0.00622 0.0061 0.0549 0.9925 7.750 0.8635 0.01247 0.00651 0.0052 0.0548 0.9942 8.000 0.8962 0.01278 0.00683 0.0042 0.0546 0.9959 8.250 0.9285 0.01309 0.00716 0.0032 0.0545 0.9977 8.500 0.9605 0.01342 0.00751 0.0023 0.0543 0.9993 8.750 0.9872 0.01375 0.00785 0.0025 0.0542 1.0000 9.000 1.0069 0.01406 0.00818 0.0041 0.0541 1.0000 9.250 1.0266 0.01438 0.00853 0.0058 0.0540 1.0000 9.500 1.0463 0.01471 0.00889 0.0074 0.0538 1.0000 9.750 1.0662 0.01504 0.00923 0.0089 0.0536 1.0000 10.000 1.0861 0.01536 0.00957 0.0105 0.0533 1.0000 10.250 1.1061 0.01566 0.00988 0.0120 0.0529 1.0000 10.500 1.1260 0.01596 0.01019 0.0135 0.0524 1.0000 10.750 1.1453 0.01630 0.01055 0.0151 0.0521 1.0000 11.000 1.1638 0.01669 0.01095 0.0167 0.0517 1.0000 11.250 1.1812 0.01714 0.01142 0.0185 0.0513 1.0000 11.500 1.1968 0.01772 0.01202 0.0206 0.0508 1.0000 11.750 1.2126 0.01828 0.01262 0.0226 0.0505 1.0000 12.000 1.2315 0.01857 0.01295 0.0241 0.0504 1.0000 12.250 1.2499 0.01888 0.01331 0.0257 0.0502 1.0000 12.500 1.2678 0.01921 0.01368 0.0274 0.0500 1.0000 12.750 1.2848 0.01958 0.01410 0.0292 0.0497 1.0000 13.000 1.2996 0.01993 0.01450 0.0314 0.0494 1.0000 13.250 1.3131 0.02029 0.01490 0.0337 0.0491 1.0000 13.500 1.3262 0.02069 0.01536 0.0361 0.0488 1.0000 13.750 1.3403 0.02109 0.01580 0.0381 0.0484 1.0000 14.000 1.3537 0.02157 0.01633 0.0401 0.0481 1.0000 14.250 1.3688 0.02197 0.01676 0.0418 0.0475 1.0000 14.500 1.3841 0.02238 0.01721 0.0434 0.0470 1.0000 14.750 1.3996 0.02280 0.01766 0.0448 0.0464 1.0000 15.000 1.4115 0.02348 0.01839 0.0466 0.0462 1.0000 15.250 1.4253 0.02406 0.01899 0.0479 0.0457 1.0000 15.500 1.4379 0.02475 0.01970 0.0493 0.0450 1.0000 15.750 1.4498 0.02554 0.02057 0.0506 0.0447 1.0000 16.000 1.4662 0.02607 0.02117 0.0515 0.0438 1.0000 16.250 1.4771 0.02701 0.02218 0.0526 0.0433 1.0000 16.500 1.4903 0.02782 0.02305 0.0535 0.0423 1.0000 16.750 1.5040 0.02863 0.02390 0.0542 0.0412 1.0000 17.000 1.5178 0.02947 0.02478 0.0548 0.0401 1.0000 17.250 1.5262 0.03080 0.02618 0.0555 0.0391 1.0000 17.500 1.5411 0.03164 0.02702 0.0558 0.0361 1.0000 17.750 1.5533 0.03276 0.02807 0.0561 0.0323 1.0000 18.000 1.5552 0.03488 0.03023 0.0562 0.0305 1.0000 18.250 1.5522 0.03764 0.03305 0.0559 0.0289 1.0000 18.500 1.5446 0.04111 0.03660 0.0551 0.0276 1.0000 18.750 1.5359 0.04492 0.04052 0.0537 0.0266 1.0000 19.000 1.5260 0.04911 0.04483 0.0519 0.0262 1.0000 19.250 1.5103 0.05426 0.05011 0.0494 0.0257 1.0000