WORTMANN FX 057-816 (fx057816-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 057-816 (fx057816-il) Reynolds number: 500,000 Max Cl/Cd: 113.34 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx057816-il-500000-n5.txt Download as CSV file: xf-fx057816-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7199 0.04967 0.04516 -0.0860 0.5845 0.0095
-13.750 -0.7601 0.04245 0.03766 -0.0892 0.5843 0.0094
-13.500 -0.7783 0.03889 0.03394 -0.0887 0.5840 0.0095
-13.250 -0.7888 0.03627 0.03118 -0.0873 0.5836 0.0096
-13.000 -0.7939 0.03422 0.02900 -0.0854 0.5831 0.0097
-12.750 -0.7961 0.03252 0.02717 -0.0831 0.5826 0.0098
-12.500 -0.7968 0.03117 0.02570 -0.0804 0.5820 0.0100
-12.250 -0.7903 0.02979 0.02416 -0.0786 0.5815 0.0101
-12.000 -0.7792 0.02856 0.02280 -0.0772 0.5808 0.0103
-11.750 -0.7665 0.02737 0.02147 -0.0758 0.5802 0.0105
-11.500 -0.7514 0.02629 0.02024 -0.0747 0.5794 0.0108
-11.250 -0.7346 0.02528 0.01908 -0.0737 0.5786 0.0111
-11.000 -0.7164 0.02435 0.01801 -0.0728 0.5779 0.0114
-10.750 -0.6968 0.02348 0.01699 -0.0721 0.5772 0.0117
-10.500 -0.6773 0.02259 0.01598 -0.0713 0.5765 0.0121
-10.250 -0.6570 0.02176 0.01505 -0.0706 0.5759 0.0126
-10.000 -0.6350 0.02105 0.01425 -0.0701 0.5753 0.0130
-9.750 -0.6122 0.02039 0.01350 -0.0696 0.5747 0.0135
-9.500 -0.5888 0.01977 0.01277 -0.0692 0.5742 0.0140
-9.250 -0.5650 0.01919 0.01208 -0.0688 0.5736 0.0146
-9.000 -0.5406 0.01866 0.01144 -0.0685 0.5731 0.0151
-8.750 -0.5165 0.01807 0.01076 -0.0681 0.5726 0.0160
-8.500 -0.4918 0.01757 0.01020 -0.0678 0.5720 0.0170
-8.250 -0.4665 0.01713 0.00970 -0.0676 0.5715 0.0181
-8.000 -0.4410 0.01674 0.00922 -0.0674 0.5710 0.0193
-7.750 -0.4154 0.01634 0.00877 -0.0672 0.5704 0.0207
-7.500 -0.3894 0.01596 0.00839 -0.0670 0.5700 0.0229
-7.250 -0.3632 0.01563 0.00804 -0.0669 0.5695 0.0252
-7.000 -0.3365 0.01536 0.00774 -0.0668 0.5689 0.0286
-6.750 -0.3088 0.01527 0.00770 -0.0669 0.5682 0.0331
-6.500 -0.2813 0.01515 0.00756 -0.0670 0.5675 0.0366
-6.250 -0.2539 0.01499 0.00734 -0.0670 0.5668 0.0385
-6.000 -0.2259 0.01494 0.00730 -0.0671 0.5662 0.0415
-5.750 -0.1975 0.01500 0.00735 -0.0673 0.5656 0.0440
-5.500 -0.1694 0.01497 0.00729 -0.0674 0.5650 0.0464
-5.250 -0.1413 0.01493 0.00720 -0.0675 0.5644 0.0487
-5.000 -0.1134 0.01485 0.00708 -0.0676 0.5638 0.0503
-4.750 -0.0851 0.01484 0.00701 -0.0678 0.5632 0.0514
-4.500 -0.0574 0.01469 0.00683 -0.0679 0.5627 0.0525
-4.250 -0.0306 0.01437 0.00650 -0.0679 0.5621 0.0551
-4.000 -0.0027 0.01428 0.00640 -0.0680 0.5616 0.0570
-3.750 0.0252 0.01416 0.00626 -0.0682 0.5611 0.0588
-3.500 0.0529 0.01400 0.00607 -0.0683 0.5606 0.0603
-3.250 0.0806 0.01383 0.00587 -0.0684 0.5601 0.0614
-3.000 0.1084 0.01367 0.00567 -0.0685 0.5595 0.0625
-2.750 0.1363 0.01351 0.00548 -0.0686 0.5590 0.0633
-2.500 0.1642 0.01338 0.00532 -0.0688 0.5584 0.0641
-2.250 0.1922 0.01326 0.00517 -0.0690 0.5579 0.0648
-2.000 0.2202 0.01316 0.00506 -0.0691 0.5574 0.0653
-1.750 0.2483 0.01309 0.00496 -0.0694 0.5570 0.0658
-1.500 0.2765 0.01304 0.00490 -0.0696 0.5565 0.0663
-1.250 0.3044 0.01293 0.00482 -0.0698 0.5560 0.0671
-1.000 0.3323 0.01282 0.00473 -0.0700 0.5555 0.0692
-0.750 0.3604 0.01277 0.00472 -0.0703 0.5549 0.0715
-0.500 0.3886 0.01274 0.00472 -0.0706 0.5543 0.0735
-0.250 0.4169 0.01273 0.00472 -0.0709 0.5537 0.0754
0.000 0.4452 0.01273 0.00475 -0.0712 0.5531 0.0771
0.250 0.4735 0.01272 0.00476 -0.0715 0.5524 0.0793
0.500 0.5019 0.01271 0.00478 -0.0718 0.5516 0.0823
0.750 0.5303 0.01271 0.00482 -0.0721 0.5508 0.0855
1.000 0.5587 0.01272 0.00486 -0.0724 0.5501 0.0904
1.250 0.5871 0.01270 0.00492 -0.0728 0.5495 0.1055
1.500 0.6139 0.01197 0.00498 -0.0736 0.5489 0.3915
1.750 0.6378 0.01108 0.00528 -0.0735 0.5484 0.7771
2.000 0.6662 0.01123 0.00545 -0.0737 0.5478 0.7989
2.250 0.6941 0.01138 0.00563 -0.0738 0.5473 0.8109
2.500 0.7218 0.01153 0.00580 -0.0738 0.5467 0.8216
2.750 0.7500 0.01169 0.00597 -0.0740 0.5462 0.8320
3.000 0.7771 0.01181 0.00613 -0.0739 0.5457 0.8378
3.250 0.8052 0.01193 0.00626 -0.0741 0.5452 0.8428
3.500 0.8343 0.01202 0.00635 -0.0746 0.5446 0.8466
3.750 0.8626 0.01206 0.00640 -0.0748 0.5438 0.8497
4.000 0.8913 0.01209 0.00643 -0.0751 0.5428 0.8517
4.250 0.9181 0.01221 0.00664 -0.0753 0.5413 0.8541
4.500 0.9449 0.01236 0.00687 -0.0753 0.5399 0.8585
4.750 0.9727 0.01244 0.00700 -0.0756 0.5380 0.8622
5.000 1.0014 0.01243 0.00702 -0.0761 0.5360 0.8635
5.250 1.0302 0.01237 0.00700 -0.0765 0.5343 0.8642
5.500 1.0591 0.01233 0.00698 -0.0769 0.5328 0.8650
5.750 1.0880 0.01227 0.00695 -0.0774 0.5315 0.8659
6.000 1.1168 0.01225 0.00696 -0.0778 0.5303 0.8668
6.250 1.1452 0.01223 0.00698 -0.0782 0.5286 0.8678
6.500 1.1715 0.01236 0.00723 -0.0784 0.5256 0.8687
6.750 1.1989 0.01240 0.00736 -0.0787 0.5227 0.8697
7.000 1.2272 0.01233 0.00735 -0.0791 0.5197 0.8706
7.250 1.2559 0.01224 0.00730 -0.0795 0.5172 0.8716
7.500 1.2837 0.01224 0.00737 -0.0798 0.5144 0.8726
7.750 1.3098 0.01234 0.00760 -0.0800 0.5076 0.8738
8.000 1.3376 0.01217 0.00747 -0.0803 0.4956 0.8749
8.250 1.3646 0.01204 0.00734 -0.0804 0.4770 0.8760
8.500 1.3816 0.01238 0.00741 -0.0791 0.4276 0.8776
8.750 1.3493 0.01528 0.00983 -0.0715 0.3390 0.8816
9.000 1.3159 0.01778 0.01233 -0.0643 0.3162 0.8867
9.250 1.2772 0.02278 0.01737 -0.0607 0.3016 0.8926
9.500 1.2494 0.02632 0.02090 -0.0569 0.2881 0.8973
9.750 1.2249 0.02960 0.02414 -0.0533 0.2722 0.9027
10.000 1.2116 0.03224 0.02675 -0.0507 0.2576 0.9078
10.250 1.2035 0.03458 0.02906 -0.0486 0.2438 0.9131
10.500 1.1992 0.03668 0.03114 -0.0468 0.2293 0.9204
10.750 1.1967 0.03893 0.03335 -0.0455 0.2111 0.9302
11.000 1.1943 0.04155 0.03585 -0.0449 0.1834 0.9470
11.500 1.1869 0.04714 0.04107 -0.0437 0.1210 1.0000
11.750 1.1883 0.04944 0.04323 -0.0430 0.1016 1.0000
12.000 1.1948 0.05134 0.04510 -0.0426 0.0914 1.0000
12.250 1.2031 0.05311 0.04684 -0.0424 0.0832 1.0000
12.500 1.2123 0.05481 0.04852 -0.0421 0.0762 1.0000
12.750 1.2220 0.05649 0.05018 -0.0420 0.0692 1.0000
13.000 1.2317 0.05819 0.05188 -0.0418 0.0608 1.0000
13.250 1.2372 0.06032 0.05393 -0.0416 0.0460 1.0000
13.500 1.2369 0.06306 0.05649 -0.0413 0.0272 1.0000
13.750 1.2446 0.06505 0.05849 -0.0412 0.0221 1.0000
14.000 1.2524 0.06707 0.06054 -0.0411 0.0197 1.0000
14.250 1.2593 0.06924 0.06275 -0.0411 0.0173 1.0000
14.500 1.2687 0.07113 0.06470 -0.0412 0.0162 1.0000
14.750 1.2777 0.07310 0.06672 -0.0413 0.0150 1.0000
15.000 1.2850 0.07529 0.06895 -0.0415 0.0142 1.0000
15.250 1.2911 0.07765 0.07136 -0.0416 0.0134 1.0000
15.500 1.2975 0.07999 0.07375 -0.0418 0.0127 1.0000
15.750 1.3055 0.08219 0.07601 -0.0421 0.0121 1.0000
16.000 1.3120 0.08461 0.07850 -0.0425 0.0115 1.0000
16.250 1.3184 0.08705 0.08100 -0.0429 0.0110 1.0000
16.500 1.3239 0.08963 0.08363 -0.0433 0.0105 1.0000
16.750 1.3272 0.09255 0.08661 -0.0438 0.0101 1.0000
17.000 1.3306 0.09548 0.08960 -0.0444 0.0097 1.0000
17.250 1.3356 0.09823 0.09243 -0.0450 0.0094 1.0000
17.500 1.3393 0.10120 0.09548 -0.0458 0.0091 1.0000
17.750 1.3433 0.10414 0.09850 -0.0465 0.0088 1.0000
18.000 1.3458 0.10735 0.10183 -0.0474 0.0086 1.0000
18.250 1.3482 0.11057 0.10512 -0.0484 0.0084 1.0000
18.500 1.3498 0.11394 0.10856 -0.0494 0.0081 1.0000
18.750 1.3512 0.11738 0.11208 -0.0506 0.0079 1.0000
19.000 1.3503 0.12121 0.11598 -0.0519 0.0077 1.0000
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Polar data table (+)
Polar graphs
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