WORTMANN FX 057-816 (fx057816-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 057-816 (fx057816-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.81 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx057816-il-1000000.txt Download as CSV file: xf-fx057816-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 057-816
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8643 0.04544 0.04152 -0.0879 0.5915 0.0119
-15.000 -0.8898 0.04041 0.03632 -0.0896 0.5911 0.0119
-14.750 -0.9058 0.03707 0.03282 -0.0892 0.5906 0.0119
-14.500 -0.9144 0.03463 0.03025 -0.0879 0.5901 0.0120
-14.250 -0.9157 0.03286 0.02837 -0.0865 0.5895 0.0122
-14.000 -0.9163 0.03123 0.02661 -0.0847 0.5889 0.0124
-13.750 -0.9164 0.02969 0.02495 -0.0826 0.5882 0.0125
-13.500 -0.9132 0.02843 0.02357 -0.0804 0.5875 0.0127
-13.250 -0.9096 0.02733 0.02235 -0.0778 0.5868 0.0128
-13.000 -0.9056 0.02637 0.02126 -0.0751 0.5858 0.0130
-12.750 -0.8934 0.02550 0.02027 -0.0735 0.5848 0.0131
-12.500 -0.8772 0.02473 0.01940 -0.0722 0.5845 0.0132
-12.250 -0.8677 0.02332 0.01782 -0.0704 0.5842 0.0135
-12.000 -0.8545 0.02214 0.01654 -0.0689 0.5837 0.0139
-11.750 -0.8363 0.02133 0.01565 -0.0678 0.5832 0.0142
-11.500 -0.8158 0.02068 0.01494 -0.0671 0.5826 0.0146
-11.250 -0.7944 0.02007 0.01426 -0.0664 0.5821 0.0150
-11.000 -0.7726 0.01947 0.01357 -0.0657 0.5815 0.0153
-10.750 -0.7493 0.01898 0.01301 -0.0652 0.5809 0.0158
-10.500 -0.7257 0.01850 0.01244 -0.0648 0.5803 0.0162
-10.250 -0.7042 0.01774 0.01159 -0.0641 0.5797 0.0167
-10.000 -0.6817 0.01707 0.01086 -0.0635 0.5791 0.0174
-9.750 -0.6574 0.01661 0.01035 -0.0631 0.5784 0.0180
-9.500 -0.6324 0.01620 0.00989 -0.0628 0.5778 0.0187
-9.250 -0.6073 0.01579 0.00942 -0.0625 0.5772 0.0194
-9.000 -0.5820 0.01539 0.00894 -0.0622 0.5766 0.0200
-8.750 -0.5576 0.01485 0.00837 -0.0618 0.5760 0.0212
-8.500 -0.5317 0.01451 0.00800 -0.0616 0.5754 0.0222
-8.250 -0.5053 0.01423 0.00767 -0.0615 0.5749 0.0233
-8.000 -0.4796 0.01384 0.00725 -0.0612 0.5743 0.0249
-7.750 -0.4530 0.01357 0.00698 -0.0611 0.5737 0.0266
-7.500 -0.4260 0.01337 0.00671 -0.0610 0.5730 0.0281
-7.250 -0.3994 0.01309 0.00646 -0.0609 0.5723 0.0307
-7.000 -0.3718 0.01298 0.00631 -0.0610 0.5716 0.0328
-6.750 -0.3445 0.01285 0.00619 -0.0610 0.5709 0.0354
-6.500 -0.3163 0.01292 0.00626 -0.0611 0.5699 0.0378
-6.250 -0.2885 0.01290 0.00624 -0.0612 0.5692 0.0399
-6.000 -0.2600 0.01287 0.00624 -0.0613 0.5689 0.0420
-5.750 -0.2311 0.01290 0.00627 -0.0616 0.5686 0.0439
-5.500 -0.2022 0.01292 0.00627 -0.0618 0.5683 0.0454
-5.250 -0.1746 0.01273 0.00606 -0.0618 0.5679 0.0473
-5.000 -0.1461 0.01269 0.00605 -0.0620 0.5675 0.0489
-4.750 -0.1174 0.01269 0.00606 -0.0622 0.5670 0.0504
-4.500 -0.0887 0.01270 0.00606 -0.0625 0.5665 0.0520
-4.250 -0.0601 0.01267 0.00602 -0.0627 0.5660 0.0533
-4.000 -0.0311 0.01273 0.00606 -0.0629 0.5654 0.0541
-3.750 -0.0049 0.01221 0.00555 -0.0628 0.5648 0.0565
-3.500 0.0235 0.01213 0.00549 -0.0630 0.5642 0.0581
-3.250 0.0519 0.01205 0.00541 -0.0632 0.5635 0.0596
-3.000 0.0802 0.01195 0.00531 -0.0634 0.5629 0.0610
-2.750 0.1086 0.01186 0.00522 -0.0636 0.5624 0.0624
-2.500 0.1371 0.01177 0.00513 -0.0638 0.5618 0.0633
-2.250 0.1657 0.01172 0.00506 -0.0641 0.5613 0.0639
-2.000 0.1928 0.01135 0.00469 -0.0642 0.5608 0.0662
-1.750 0.2210 0.01121 0.00454 -0.0644 0.5602 0.0679
-1.500 0.2496 0.01111 0.00445 -0.0647 0.5598 0.0694
-1.250 0.2782 0.01103 0.00438 -0.0649 0.5593 0.0709
-1.000 0.3070 0.01097 0.00431 -0.0652 0.5588 0.0725
-0.750 0.3358 0.01093 0.00427 -0.0656 0.5583 0.0741
-0.500 0.3647 0.01090 0.00424 -0.0659 0.5578 0.0752
-0.250 0.3934 0.01082 0.00415 -0.0662 0.5572 0.0771
0.000 0.4222 0.01076 0.00409 -0.0665 0.5566 0.0803
0.250 0.4510 0.01076 0.00410 -0.0669 0.5560 0.0833
0.500 0.4796 0.01083 0.00418 -0.0672 0.5552 0.0863
0.750 0.5076 0.01105 0.00443 -0.0675 0.5542 0.0902
1.000 0.5365 0.01099 0.00444 -0.0679 0.5539 0.1032
1.250 0.5626 0.00928 0.00435 -0.0692 0.5536 0.6667
1.500 0.5898 0.00924 0.00466 -0.0691 0.5532 0.7945
1.750 0.6185 0.00938 0.00483 -0.0693 0.5528 0.8090
2.000 0.6473 0.00954 0.00500 -0.0696 0.5523 0.8193
2.250 0.6752 0.00966 0.00517 -0.0696 0.5518 0.8268
2.500 0.7038 0.00978 0.00531 -0.0698 0.5510 0.8332
2.750 0.7324 0.00984 0.00539 -0.0700 0.5501 0.8385
3.000 0.7607 0.00984 0.00543 -0.0701 0.5489 0.8424
3.250 0.7893 0.00987 0.00548 -0.0704 0.5478 0.8464
3.500 0.8181 0.00993 0.00556 -0.0707 0.5469 0.8505
3.750 0.8464 0.00997 0.00562 -0.0709 0.5461 0.8550
4.000 0.8742 0.00999 0.00567 -0.0709 0.5452 0.8589
4.250 0.9035 0.00990 0.00558 -0.0713 0.5439 0.8616
4.500 0.9333 0.00981 0.00548 -0.0717 0.5426 0.8638
4.750 0.9625 0.00987 0.00553 -0.0722 0.5417 0.8666
5.000 0.9919 0.00996 0.00561 -0.0727 0.5403 0.8675
5.250 1.0209 0.00990 0.00560 -0.0732 0.5383 0.8681
5.500 1.0500 0.00978 0.00553 -0.0737 0.5367 0.8691
5.750 1.0790 0.00976 0.00555 -0.0742 0.5353 0.8699
6.000 1.1079 0.00974 0.00558 -0.0747 0.5340 0.8707
6.250 1.1371 0.00968 0.00555 -0.0752 0.5324 0.8714
6.500 1.1668 0.00953 0.00542 -0.0757 0.5303 0.8722
6.750 1.1965 0.00935 0.00524 -0.0763 0.5279 0.8729
7.000 1.2255 0.00922 0.00513 -0.0767 0.5241 0.8737
7.250 1.2542 0.00908 0.00508 -0.0771 0.5199 0.8746
7.500 1.2835 0.00890 0.00492 -0.0776 0.5146 0.8755
7.750 1.3121 0.00884 0.00489 -0.0780 0.5094 0.8764
8.000 1.3406 0.00878 0.00489 -0.0785 0.5003 0.8774
8.250 1.3680 0.00878 0.00487 -0.0787 0.4836 0.8786
8.500 1.3859 0.00945 0.00528 -0.0776 0.4258 0.8801
8.750 1.3689 0.01240 0.00761 -0.0721 0.3097 0.8825
9.000 1.3650 0.01408 0.00910 -0.0683 0.2690 0.8844
9.250 1.3576 0.01545 0.01043 -0.0640 0.2491 0.8875
9.500 1.3348 0.01837 0.01344 -0.0598 0.2400 0.8919
9.750 1.3119 0.02200 0.01712 -0.0568 0.2320 0.8963
10.000 1.2921 0.02494 0.02005 -0.0533 0.2207 0.9007
10.250 1.2766 0.02752 0.02263 -0.0502 0.2089 0.9054
10.500 1.2616 0.03013 0.02520 -0.0474 0.1918 0.9102
10.750 1.2457 0.03293 0.02791 -0.0447 0.1712 0.9153
11.000 1.2316 0.03559 0.03045 -0.0422 0.1440 0.9223
11.250 1.2196 0.03840 0.03313 -0.0401 0.1165 0.9316
11.500 1.2210 0.04033 0.03504 -0.0390 0.1002 0.9506
11.750 1.2331 0.04226 0.03694 -0.0401 0.0872 1.0000
12.000 1.2400 0.04406 0.03869 -0.0396 0.0796 1.0000
12.250 1.2506 0.04554 0.04018 -0.0394 0.0741 1.0000
12.500 1.2589 0.04721 0.04181 -0.0390 0.0668 1.0000
12.750 1.2688 0.04876 0.04333 -0.0387 0.0589 1.0000
13.000 1.2742 0.05073 0.04520 -0.0383 0.0456 1.0000
13.250 1.2751 0.05316 0.04751 -0.0378 0.0309 1.0000
13.500 1.2811 0.05516 0.04947 -0.0375 0.0252 1.0000
13.750 1.2883 0.05707 0.05137 -0.0372 0.0223 1.0000
14.000 1.2982 0.05877 0.05310 -0.0371 0.0207 1.0000
14.250 1.3052 0.06080 0.05514 -0.0370 0.0194 1.0000
14.500 1.3119 0.06287 0.05725 -0.0369 0.0182 1.0000
14.750 1.3222 0.06460 0.05902 -0.0369 0.0175 1.0000
15.000 1.3319 0.06639 0.06085 -0.0370 0.0166 1.0000
15.250 1.3385 0.06858 0.06307 -0.0370 0.0159 1.0000
15.500 1.3430 0.07102 0.06555 -0.0371 0.0151 1.0000
15.750 1.3495 0.07326 0.06784 -0.0372 0.0147 1.0000
16.000 1.3585 0.07527 0.06991 -0.0374 0.0143 1.0000
16.250 1.3658 0.07751 0.07220 -0.0377 0.0138 1.0000
16.500 1.3730 0.07975 0.07449 -0.0380 0.0134 1.0000
16.750 1.3797 0.08207 0.07686 -0.0383 0.0130 1.0000
17.000 1.3826 0.08495 0.07978 -0.0388 0.0125 1.0000
17.250 1.3843 0.08802 0.08291 -0.0393 0.0121 1.0000
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Polar data table (+)
Polar graphs
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