WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 50,000 Max Cl/Cd: 8.28 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617ai-il-50000-n5.txt Download as CSV file: xf-fx6617ai-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3790 0.09630 0.09030 -0.0687 0.9577 0.0525
-11.500 -0.3856 0.08892 0.08282 -0.0751 0.9134 0.0522
-11.250 -0.3985 0.08168 0.07541 -0.0812 0.8838 0.0518
-11.000 -0.4152 0.07536 0.06886 -0.0860 0.8601 0.0515
-10.750 -0.4327 0.07006 0.06330 -0.0894 0.8400 0.0512
-10.500 -0.4485 0.06557 0.05851 -0.0918 0.8230 0.0511
-10.250 -0.4619 0.06175 0.05436 -0.0931 0.8086 0.0510
-10.000 -0.4726 0.05861 0.05087 -0.0932 0.7967 0.0510
-9.750 -0.4764 0.05553 0.04740 -0.0931 0.7859 0.0513
-9.500 -0.4759 0.05269 0.04410 -0.0929 0.7762 0.0518
-9.250 -0.4703 0.05009 0.04105 -0.0924 0.7680 0.0528
-9.000 -0.4551 0.04796 0.03882 -0.0923 0.7593 0.0544
-8.750 -0.4394 0.04607 0.03668 -0.0919 0.7523 0.0562
-8.500 -0.4215 0.04418 0.03454 -0.0916 0.7447 0.0579
-8.250 -0.4006 0.04233 0.03235 -0.0910 0.7382 0.0594
-8.000 -0.3769 0.04072 0.03043 -0.0905 0.7319 0.0613
-7.750 -0.3520 0.03941 0.02883 -0.0899 0.7256 0.0641
-7.500 -0.3279 0.03828 0.02771 -0.0892 0.7206 0.0681
-7.250 -0.3039 0.03738 0.02667 -0.0885 0.7148 0.0725
-7.000 -0.2805 0.03655 0.02565 -0.0874 0.7095 0.0766
-6.750 -0.2629 0.03557 0.02469 -0.0864 0.7051 0.0822
-6.500 -0.2456 0.03477 0.02380 -0.0855 0.7000 0.0904
-6.250 -0.2314 0.03380 0.02287 -0.0846 0.6950 0.1000
-6.000 -0.2176 0.03268 0.02178 -0.0837 0.6909 0.1157
-5.750 -0.2058 0.03124 0.02059 -0.0830 0.6873 0.1473
-5.500 -0.1993 0.02945 0.01958 -0.0825 0.6827 0.2355
-5.250 -0.1885 0.02909 0.02034 -0.0796 0.6785 0.4003
-5.000 -0.1669 0.02986 0.02108 -0.0776 0.6748 0.4811
-4.750 -0.1453 0.03149 0.02259 -0.0745 0.6713 0.5412
-4.500 -0.1264 0.03312 0.02413 -0.0713 0.6665 0.5789
-4.250 -0.1046 0.03401 0.02485 -0.0690 0.6626 0.6001
-4.000 -0.0817 0.03445 0.02506 -0.0675 0.6594 0.6163
-3.750 -0.0582 0.03454 0.02487 -0.0667 0.6568 0.6304
-3.500 -0.0382 0.03492 0.02513 -0.0656 0.6526 0.6402
-3.250 -0.0181 0.03511 0.02517 -0.0648 0.6485 0.6505
-3.000 0.0035 0.03511 0.02496 -0.0645 0.6451 0.6621
-2.750 0.0273 0.03522 0.02489 -0.0635 0.6423 0.6708
-2.500 0.0494 0.03528 0.02478 -0.0631 0.6395 0.6806
-2.250 0.0657 0.03570 0.02513 -0.0624 0.6353 0.6893
-2.000 0.0854 0.03593 0.02525 -0.0620 0.6318 0.6969
-1.750 0.1078 0.03603 0.02520 -0.0618 0.6287 0.7044
-1.500 0.1324 0.03601 0.02500 -0.0619 0.6262 0.7115
-1.250 0.1531 0.03628 0.02517 -0.0615 0.6231 0.7180
-1.000 0.1665 0.03699 0.02585 -0.0613 0.6185 0.7254
-0.750 0.1846 0.03746 0.02627 -0.0607 0.6152 0.7311
-0.500 0.2076 0.03773 0.02640 -0.0610 0.6124 0.7383
-0.250 0.2327 0.03785 0.02641 -0.0610 0.6102 0.7442
0.000 0.2496 0.03852 0.02702 -0.0607 0.6067 0.7506
0.250 0.2571 0.03982 0.02833 -0.0601 0.6014 0.7574
0.500 0.2742 0.04053 0.02901 -0.0596 0.5982 0.7634
0.750 0.2982 0.04098 0.02936 -0.0602 0.5958 0.7705
1.000 0.3233 0.04121 0.02952 -0.0601 0.5938 0.7764
1.250 0.3200 0.04339 0.03177 -0.0590 0.5875 0.7833
1.500 0.3316 0.04464 0.03302 -0.0586 0.5833 0.7898
1.750 0.3514 0.04540 0.03374 -0.0586 0.5807 0.7966
2.000 0.3766 0.04586 0.03415 -0.0590 0.5786 0.8038
2.500 0.3742 0.05022 0.03860 -0.0573 0.5675 0.8184
2.750 0.3922 0.05115 0.03953 -0.0571 0.5648 0.8259
3.000 0.4173 0.05173 0.04009 -0.0575 0.5628 0.8342
3.500 0.4210 0.05600 0.04446 -0.0564 0.5527 0.8519
3.750 0.4382 0.05709 0.04558 -0.0564 0.5498 0.8623
4.000 0.4611 0.05777 0.04630 -0.0564 0.5475 0.8732
4.250 0.4843 0.05846 0.04702 -0.0564 0.5452 0.8862
4.500 0.4704 0.06165 0.05035 -0.0556 0.5381 0.9025
5.000 0.5143 0.06375 0.05257 -0.0574 0.5320 1.0002
5.500 0.5329 0.06825 0.05708 -0.0593 0.5225 1.0002
5.750 0.5534 0.06978 0.05859 -0.0605 0.5190 1.0002
6.000 0.5807 0.07089 0.05968 -0.0617 0.5163 1.0002
6.250 0.5883 0.07321 0.06203 -0.0622 0.5116 1.0002
6.500 0.5944 0.07556 0.06440 -0.0626 0.5064 1.0002
6.750 0.6154 0.07699 0.06583 -0.0634 0.5029 1.0002
7.000 0.6422 0.07808 0.06693 -0.0642 0.5004 1.0002
7.250 0.6370 0.08113 0.07004 -0.0641 0.4941 1.0002
7.500 0.6505 0.08298 0.07192 -0.0644 0.4896 1.0002
7.750 0.6737 0.08425 0.07322 -0.0650 0.4865 1.0002
8.000 0.6845 0.08634 0.07535 -0.0652 0.4823 1.0002
8.250 0.6853 0.08898 0.07804 -0.0651 0.4762 1.0002
8.500 0.7050 0.09045 0.07958 -0.0655 0.4726 1.0002
8.750 0.7308 0.09159 0.08077 -0.0659 0.4701 1.0002
9.000 0.7195 0.09505 0.08430 -0.0656 0.4627 1.0002
9.250 0.7360 0.09672 0.08605 -0.0659 0.4585 1.0002
9.500 0.7606 0.09790 0.08732 -0.0662 0.4557 1.0002
9.750 0.7523 0.10123 0.09073 -0.0660 0.4486 1.0002
10.000 0.7668 0.10303 0.09262 -0.0662 0.4441 1.0002
10.250 0.7913 0.10421 0.09390 -0.0664 0.4411 1.0002
10.500 0.7830 0.10753 0.09730 -0.0664 0.4337 1.0002
10.750 0.7986 0.10926 0.09916 -0.0665 0.4291 1.0002
11.000 0.8244 0.11034 0.10036 -0.0667 0.4262 1.0002
11.250 0.8130 0.11375 0.10385 -0.0667 0.4176 1.0002
11.500 0.8333 0.11514 0.10537 -0.0668 0.4134 1.0002
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Polar data table (+)
Polar graphs
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