WORTMANN FX 69-274 (fx69274-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 69-274 (fx69274-il) Reynolds number: 200,000 Max Cl/Cd: 35.95 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69274-il-200000.txt Download as CSV file: xf-fx69274-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 69-274
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
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9096 0.08851 0.08278 -0.0746 1.0000 0.0732
-19.500 -0.9039 0.08592 0.08018 -0.0761 1.0000 0.0744
-19.250 -0.9072 0.08217 0.07632 -0.0781 1.0000 0.0755
-19.000 -0.9139 0.07801 0.07200 -0.0803 1.0000 0.0767
-18.750 -0.9220 0.07377 0.06757 -0.0826 1.0000 0.0778
-18.500 -0.9246 0.07023 0.06387 -0.0845 1.0000 0.0789
-18.250 -0.8985 0.06992 0.06374 -0.0849 1.0000 0.0806
-18.000 -0.8862 0.06800 0.06184 -0.0865 1.0000 0.0821
-17.750 -0.8804 0.06535 0.05911 -0.0884 1.0000 0.0837
-17.500 -0.8796 0.06234 0.05593 -0.0907 0.9860 0.0853
-17.250 -0.8656 0.06023 0.05372 -0.0929 0.9689 0.0871
-17.000 -0.8449 0.05931 0.05286 -0.0938 0.9537 0.0890
-16.750 -0.8364 0.05780 0.05130 -0.0937 0.9392 0.0908
-16.500 -0.8339 0.05596 0.04934 -0.0933 0.9266 0.0927
-16.250 -0.8355 0.05387 0.04704 -0.0926 0.9152 0.0943
-16.000 -0.8202 0.05318 0.04642 -0.0917 0.9052 0.0965
-15.750 -0.8127 0.05198 0.04520 -0.0908 0.8959 0.0986
-15.500 -0.8062 0.05032 0.04347 -0.0907 0.8868 0.1012
-15.250 -0.8049 0.04836 0.04130 -0.0902 0.8782 0.1035
-15.000 -0.7905 0.04759 0.04063 -0.0894 0.8705 0.1064
-14.750 -0.7818 0.04614 0.03916 -0.0892 0.8623 0.1095
-14.500 -0.7779 0.04447 0.03732 -0.0886 0.8553 0.1128
-14.250 -0.7647 0.04344 0.03636 -0.0881 0.8478 0.1163
-14.000 -0.7559 0.04206 0.03496 -0.0877 0.8398 0.1200
-13.750 -0.7509 0.04053 0.03323 -0.0869 0.8331 0.1240
-13.500 -0.7381 0.03947 0.03230 -0.0864 0.8263 0.1284
-13.250 -0.7292 0.03809 0.03085 -0.0861 0.8192 0.1334
-13.000 -0.7198 0.03688 0.02966 -0.0853 0.8131 0.1383
-12.750 -0.7119 0.03565 0.02838 -0.0845 0.8075 0.1436
-12.500 -0.7011 0.03438 0.02711 -0.0842 0.8005 0.1496
-12.250 -0.6929 0.03311 0.02586 -0.0835 0.7940 0.1557
-12.000 -0.6845 0.03191 0.02461 -0.0825 0.7886 0.1626
-11.750 -0.6762 0.03073 0.02345 -0.0818 0.7831 0.1700
-11.500 -0.6665 0.02956 0.02231 -0.0812 0.7766 0.1780
-11.250 -0.6571 0.02847 0.02119 -0.0804 0.7708 0.1871
-11.000 -0.6496 0.02735 0.02009 -0.0791 0.7659 0.1960
-10.750 -0.6396 0.02641 0.01911 -0.0781 0.7609 0.2065
-10.500 -0.6299 0.02542 0.01819 -0.0772 0.7545 0.2178
-10.250 -0.6212 0.02445 0.01727 -0.0759 0.7486 0.2294
-10.000 -0.6117 0.02358 0.01638 -0.0744 0.7437 0.2422
-9.750 -0.6013 0.02287 0.01563 -0.0730 0.7390 0.2562
-9.500 -0.5904 0.02218 0.01502 -0.0718 0.7330 0.2706
-9.250 -0.5791 0.02154 0.01443 -0.0703 0.7274 0.2845
-9.000 -0.5672 0.02098 0.01387 -0.0686 0.7227 0.2984
-8.750 -0.5566 0.02061 0.01342 -0.0664 0.7185 0.3125
-8.500 -0.5480 0.02040 0.01327 -0.0639 0.7132 0.3260
-8.250 -0.5364 0.02020 0.01312 -0.0617 0.7073 0.3393
-8.000 -0.5218 0.01998 0.01287 -0.0599 0.7024 0.3533
-7.750 -0.5055 0.01980 0.01262 -0.0582 0.6983 0.3672
-7.500 -0.4857 0.01967 0.01248 -0.0570 0.6947 0.3794
-7.250 -0.4690 0.01962 0.01241 -0.0555 0.6893 0.3917
-7.000 -0.4481 0.01951 0.01238 -0.0546 0.6841 0.4027
-6.750 -0.4271 0.01935 0.01214 -0.0536 0.6795 0.4142
-6.500 -0.4035 0.01920 0.01196 -0.0529 0.6757 0.4253
-6.250 -0.3802 0.01913 0.01181 -0.0522 0.6720 0.4363
-6.000 -0.3596 0.01915 0.01191 -0.0513 0.6668 0.4470
-5.750 -0.3372 0.01910 0.01187 -0.0505 0.6620 0.4578
-5.500 -0.3129 0.01904 0.01180 -0.0499 0.6578 0.4689
-5.250 -0.2869 0.01892 0.01160 -0.0496 0.6541 0.4790
-5.000 -0.2599 0.01895 0.01158 -0.0495 0.6505 0.4885
-4.750 -0.2400 0.01899 0.01163 -0.0484 0.6453 0.4980
-4.500 -0.2144 0.01899 0.01171 -0.0481 0.6403 0.5066
-4.250 -0.1909 0.01894 0.01152 -0.0474 0.6361 0.5177
-4.000 -0.1607 0.01887 0.01148 -0.0477 0.6324 0.5273
-3.750 -0.1351 0.01894 0.01143 -0.0474 0.6289 0.5381
-3.500 -0.1123 0.01900 0.01162 -0.0467 0.6240 0.5459
-3.250 -0.0873 0.01908 0.01172 -0.0464 0.6196 0.5542
-3.000 -0.0626 0.01904 0.01158 -0.0460 0.6159 0.5635
-2.750 -0.0321 0.01901 0.01158 -0.0464 0.6126 0.5708
-2.500 -0.0030 0.01904 0.01151 -0.0467 0.6096 0.5799
-2.250 0.0198 0.01917 0.01166 -0.0461 0.6054 0.5882
-2.000 0.0433 0.01933 0.01193 -0.0454 0.6007 0.5960
-1.750 0.0674 0.01937 0.01191 -0.0450 0.5966 0.6058
-1.500 0.0964 0.01935 0.01189 -0.0452 0.5932 0.6132
-1.250 0.1269 0.01939 0.01189 -0.0456 0.5903 0.6213
-1.000 0.1551 0.01950 0.01184 -0.0459 0.5874 0.6308
-0.750 0.1757 0.01972 0.01225 -0.0449 0.5831 0.6371
-0.500 0.1986 0.01991 0.01249 -0.0443 0.5789 0.6447
-0.250 0.2227 0.01995 0.01246 -0.0440 0.5753 0.6539
0.000 0.2530 0.01999 0.01253 -0.0443 0.5722 0.6604
0.250 0.2842 0.02005 0.01254 -0.0449 0.5695 0.6684
0.500 0.3122 0.02021 0.01259 -0.0452 0.5666 0.6777
0.750 0.3298 0.02056 0.01313 -0.0437 0.5622 0.6841
1.000 0.3518 0.02079 0.01341 -0.0429 0.5579 0.6920
1.250 0.3772 0.02081 0.01336 -0.0428 0.5543 0.7008
1.500 0.4081 0.02085 0.01340 -0.0432 0.5514 0.7066
1.750 0.4406 0.02094 0.01344 -0.0440 0.5488 0.7138
2.000 0.4639 0.02121 0.01367 -0.0437 0.5455 0.7227
2.250 0.4783 0.02155 0.01416 -0.0418 0.5407 0.7284
2.500 0.5004 0.02174 0.01439 -0.0410 0.5364 0.7348
2.750 0.5284 0.02174 0.01434 -0.0412 0.5330 0.7430
3.000 0.5602 0.02170 0.01424 -0.0420 0.5303 0.7500
3.250 0.5947 0.02188 0.01435 -0.0430 0.5276 0.7558
3.500 0.6039 0.02237 0.01498 -0.0405 0.5233 0.7635
3.750 0.6180 0.02268 0.01534 -0.0389 0.5188 0.7717
4.000 0.6400 0.02288 0.01560 -0.0380 0.5153 0.7773
4.250 0.6686 0.02296 0.01565 -0.0382 0.5125 0.7845
4.500 0.7022 0.02296 0.01555 -0.0395 0.5100 0.7933
4.750 0.7354 0.02318 0.01573 -0.0403 0.5075 0.7985
5.000 0.7320 0.02392 0.01668 -0.0359 0.5031 0.8066
5.250 0.7416 0.02441 0.01723 -0.0339 0.4991 0.8159
5.500 0.7597 0.02464 0.01751 -0.0324 0.4958 0.8220
5.750 0.7895 0.02463 0.01747 -0.0328 0.4931 0.8295
6.000 0.8272 0.02452 0.01726 -0.0345 0.4908 0.8373
6.250 0.8584 0.02473 0.01745 -0.0350 0.4882 0.8427
6.500 0.8300 0.02592 0.01888 -0.0275 0.4834 0.8542
6.750 0.8269 0.02687 0.01995 -0.0237 0.4792 0.8630
7.000 0.8446 0.02723 0.02032 -0.0227 0.4762 0.8732
7.250 0.8729 0.02712 0.02021 -0.0226 0.4740 0.8813
7.500 0.9112 0.02684 0.01985 -0.0239 0.4720 0.8895
7.750 0.9564 0.02660 0.01952 -0.0264 0.4700 0.8955
8.000 0.8468 0.03150 0.02491 -0.0115 0.4606 0.9162
8.250 0.8587 0.03202 0.02546 -0.0099 0.4573 0.9280
8.500 0.8888 0.03169 0.02512 -0.0100 0.4554 0.9392
8.750 0.9314 0.03097 0.02435 -0.0115 0.4540 0.9480
9.000 0.9815 0.03022 0.02353 -0.0142 0.4526 0.9561
9.250 0.8511 0.04141 0.03521 -0.0067 0.4364 0.9850
9.500 0.9122 0.03968 0.03343 -0.0106 0.4362 0.9974
9.750 0.9601 0.03833 0.03202 -0.0128 0.4355 1.0000
10.000 1.0120 0.03692 0.03054 -0.0153 0.4348 1.0000
10.250 1.0693 0.03544 0.02898 -0.0184 0.4340 1.0000
10.500 0.8912 0.05096 0.04483 -0.0086 0.4145 1.0000
10.750 0.9412 0.04911 0.04293 -0.0104 0.4146 1.0000
11.000 0.9948 0.04705 0.04082 -0.0123 0.4146 1.0000
11.250 1.0541 0.04471 0.03841 -0.0147 0.4148 1.0000
11.500 0.5900 0.09827 0.09256 -0.0055 0.3496 1.0000
11.750 0.6187 0.09817 0.09245 -0.0061 0.3486 1.0000
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Polar data table (+)
Polar graphs
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