WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.67 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617ai-il-1000000-n5.txt Download as CSV file: xf-fx6617ai-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.7885 0.12011 0.11784 -0.0305 0.9998 0.0076
-18.250 -0.8268 0.10868 0.10624 -0.0365 0.9998 0.0076
-18.000 -0.8573 0.09900 0.09642 -0.0417 0.9998 0.0076
-17.750 -0.8818 0.09071 0.08799 -0.0462 0.9998 0.0076
-17.500 -0.9001 0.08363 0.08040 -0.0505 0.8446 0.0076
-17.250 -0.9162 0.07761 0.07399 -0.0536 0.7753 0.0076
-17.000 -0.9292 0.07192 0.06807 -0.0567 0.7462 0.0077
-16.750 -0.9446 0.06611 0.06206 -0.0599 0.7245 0.0077
-16.500 -0.9564 0.06103 0.05679 -0.0626 0.7046 0.0078
-16.250 -0.9644 0.05661 0.05221 -0.0649 0.6872 0.0079
-15.750 -0.9714 0.04948 0.04480 -0.0683 0.6596 0.0081
-15.500 -0.9722 0.04652 0.04172 -0.0695 0.6492 0.0081
-15.250 -0.9705 0.04389 0.03898 -0.0706 0.6394 0.0082
-15.000 -0.9669 0.04152 0.03651 -0.0714 0.6306 0.0083
-14.750 -0.9618 0.03935 0.03424 -0.0722 0.6228 0.0084
-14.500 -0.9554 0.03734 0.03214 -0.0729 0.6156 0.0085
-14.250 -0.9476 0.03550 0.03020 -0.0734 0.6090 0.0086
-14.000 -0.9387 0.03377 0.02839 -0.0740 0.6039 0.0087
-13.750 -0.9288 0.03215 0.02669 -0.0744 0.5987 0.0088
-13.250 -0.9061 0.02918 0.02355 -0.0752 0.5901 0.0091
-13.000 -0.8933 0.02782 0.02211 -0.0756 0.5861 0.0092
-12.750 -0.8796 0.02653 0.02074 -0.0760 0.5821 0.0094
-12.250 -0.8494 0.02415 0.01819 -0.0768 0.5749 0.0097
-12.000 -0.8328 0.02305 0.01701 -0.0774 0.5715 0.0098
-11.750 -0.8165 0.02202 0.01590 -0.0778 0.5679 0.0099
-11.500 -0.8000 0.02121 0.01499 -0.0778 0.5646 0.0100
-11.000 -0.7583 0.01994 0.01358 -0.0779 0.5593 0.0102
-10.750 -0.7383 0.01915 0.01272 -0.0778 0.5568 0.0104
-10.500 -0.7177 0.01838 0.01189 -0.0777 0.5542 0.0107
-10.250 -0.6951 0.01779 0.01125 -0.0777 0.5516 0.0109
-10.000 -0.6716 0.01729 0.01069 -0.0778 0.5490 0.0112
-9.750 -0.6475 0.01682 0.01016 -0.0778 0.5463 0.0113
-9.500 -0.6229 0.01637 0.00967 -0.0779 0.5442 0.0115
-9.250 -0.5979 0.01593 0.00918 -0.0780 0.5419 0.0117
-9.000 -0.5727 0.01551 0.00872 -0.0780 0.5395 0.0119
-8.750 -0.5472 0.01510 0.00826 -0.0781 0.5371 0.0122
-8.500 -0.5215 0.01472 0.00782 -0.0782 0.5348 0.0124
-8.250 -0.4954 0.01437 0.00742 -0.0784 0.5326 0.0126
-7.750 -0.4422 0.01376 0.00673 -0.0787 0.5288 0.0132
-7.500 -0.4151 0.01349 0.00642 -0.0789 0.5271 0.0134
-7.250 -0.3889 0.01307 0.00596 -0.0790 0.5252 0.0139
-7.000 -0.3620 0.01274 0.00560 -0.0792 0.5231 0.0144
-6.750 -0.3348 0.01247 0.00529 -0.0794 0.5209 0.0149
-6.500 -0.3074 0.01222 0.00501 -0.0796 0.5186 0.0154
-6.250 -0.2798 0.01201 0.00475 -0.0798 0.5165 0.0160
-6.000 -0.2521 0.01181 0.00452 -0.0800 0.5146 0.0166
-5.750 -0.2240 0.01161 0.00429 -0.0803 0.5133 0.0172
-5.500 -0.1961 0.01138 0.00406 -0.0806 0.5117 0.0186
-5.250 -0.1680 0.01119 0.00386 -0.0808 0.5101 0.0202
-5.000 -0.1397 0.01102 0.00368 -0.0811 0.5084 0.0219
-4.750 -0.1115 0.01084 0.00349 -0.0814 0.5065 0.0254
-4.500 -0.0833 0.01068 0.00333 -0.0817 0.5046 0.0298
-4.250 -0.0550 0.01053 0.00317 -0.0820 0.5026 0.0353
-4.000 -0.0269 0.01036 0.00301 -0.0823 0.5006 0.0442
-3.750 0.0008 0.01007 0.00283 -0.0826 0.4991 0.0720
-3.500 0.0286 0.00978 0.00266 -0.0829 0.4978 0.1068
-3.250 0.0559 0.00938 0.00246 -0.0832 0.4965 0.1640
-3.000 0.0826 0.00886 0.00224 -0.0835 0.4950 0.2482
-2.750 0.1087 0.00826 0.00201 -0.0838 0.4935 0.3531
-2.500 0.1361 0.00792 0.00191 -0.0841 0.4919 0.4313
-2.250 0.1650 0.00784 0.00187 -0.0845 0.4902 0.4555
-2.000 0.1937 0.00776 0.00185 -0.0848 0.4884 0.4834
-1.750 0.2225 0.00771 0.00185 -0.0851 0.4866 0.5082
-1.500 0.2516 0.00773 0.00185 -0.0855 0.4847 0.5195
-1.250 0.2810 0.00773 0.00185 -0.0859 0.4836 0.5270
-1.000 0.3105 0.00774 0.00185 -0.0863 0.4825 0.5348
-0.750 0.3399 0.00774 0.00187 -0.0867 0.4812 0.5422
-0.500 0.3694 0.00777 0.00188 -0.0872 0.4798 0.5492
-0.250 0.3987 0.00779 0.00190 -0.0876 0.4783 0.5552
0.000 0.4280 0.00782 0.00192 -0.0880 0.4767 0.5603
0.250 0.4574 0.00786 0.00194 -0.0884 0.4750 0.5640
0.500 0.4866 0.00789 0.00196 -0.0888 0.4734 0.5677
0.750 0.5157 0.00794 0.00200 -0.0892 0.4717 0.5716
1.000 0.5447 0.00800 0.00204 -0.0896 0.4701 0.5753
1.250 0.5740 0.00804 0.00208 -0.0901 0.4690 0.5786
1.500 0.6034 0.00808 0.00212 -0.0905 0.4680 0.5815
1.750 0.6327 0.00811 0.00217 -0.0909 0.4667 0.5848
2.000 0.6619 0.00814 0.00223 -0.0914 0.4653 0.5883
2.250 0.6910 0.00819 0.00228 -0.0918 0.4637 0.5917
2.500 0.7202 0.00824 0.00233 -0.0922 0.4620 0.5947
2.750 0.7492 0.00830 0.00239 -0.0926 0.4605 0.5972
3.000 0.7780 0.00835 0.00246 -0.0930 0.4591 0.6000
3.250 0.8068 0.00842 0.00253 -0.0934 0.4577 0.6031
3.500 0.8354 0.00850 0.00262 -0.0938 0.4561 0.6063
3.750 0.8641 0.00857 0.00271 -0.0941 0.4546 0.6094
4.000 0.8932 0.00863 0.00279 -0.0946 0.4534 0.6120
4.250 0.9221 0.00868 0.00288 -0.0950 0.4520 0.6144
4.500 0.9508 0.00873 0.00297 -0.0954 0.4507 0.6172
4.750 0.9795 0.00880 0.00307 -0.0958 0.4492 0.6204
5.000 1.0081 0.00887 0.00318 -0.0962 0.4476 0.6234
5.250 1.0366 0.00895 0.00328 -0.0965 0.4459 0.6263
5.500 1.0649 0.00904 0.00339 -0.0969 0.4442 0.6287
5.750 1.0929 0.00913 0.00351 -0.0972 0.4423 0.6316
6.000 1.1208 0.00922 0.00364 -0.0975 0.4395 0.6348
6.250 1.1493 0.00928 0.00375 -0.0978 0.4368 0.6379
6.500 1.1774 0.00935 0.00386 -0.0981 0.4318 0.6411
6.750 1.2042 0.00950 0.00399 -0.0983 0.4257 0.6441
7.000 1.2323 0.00956 0.00411 -0.0986 0.4197 0.6473
7.250 1.2586 0.00973 0.00427 -0.0987 0.4105 0.6510
7.500 1.2859 0.00985 0.00443 -0.0989 0.4032 0.6549
7.750 1.3119 0.01004 0.00463 -0.0989 0.3946 0.6588
8.000 1.3374 0.01027 0.00485 -0.0988 0.3839 0.6623
8.250 1.3609 0.01061 0.00516 -0.0985 0.3656 0.6664
8.500 1.3785 0.01133 0.00572 -0.0973 0.3295 0.6706
8.750 1.3830 0.01284 0.00687 -0.0942 0.2681 0.6745
9.000 1.3615 0.01537 0.00888 -0.0873 0.1784 0.6782
9.250 1.3309 0.01837 0.01153 -0.0803 0.1085 0.6828
9.500 1.3121 0.02152 0.01453 -0.0768 0.0677 0.6879
9.750 1.3095 0.02412 0.01709 -0.0756 0.0507 0.6927
10.000 1.3120 0.02648 0.01949 -0.0750 0.0419 0.6978
10.250 1.3156 0.02884 0.02189 -0.0746 0.0363 0.7035
10.750 1.3207 0.03375 0.02690 -0.0737 0.0271 0.7153
11.000 1.3204 0.03643 0.02962 -0.0731 0.0233 0.7224
11.250 1.3224 0.03885 0.03209 -0.0725 0.0211 0.7294
11.500 1.3233 0.04136 0.03465 -0.0718 0.0193 0.7373
11.750 1.3245 0.04379 0.03715 -0.0712 0.0181 0.7450
12.000 1.3267 0.04613 0.03957 -0.0706 0.0172 0.7538
12.250 1.3285 0.04854 0.04205 -0.0700 0.0163 0.7635
12.500 1.3299 0.05105 0.04464 -0.0695 0.0154 0.7752
12.750 1.3327 0.05343 0.04712 -0.0690 0.0146 0.7919
13.000 1.3364 0.05574 0.04959 -0.0687 0.0141 0.8244
13.250 1.3389 0.05765 0.05183 -0.0678 0.0135 1.0002
13.500 1.3421 0.06012 0.05434 -0.0674 0.0128 1.0002
13.750 1.3455 0.06260 0.05685 -0.0672 0.0120 1.0002
14.000 1.3482 0.06516 0.05945 -0.0669 0.0113 1.0002
14.250 1.3526 0.06758 0.06191 -0.0667 0.0107 1.0002
14.500 1.3572 0.06993 0.06430 -0.0665 0.0100 1.0002
14.750 1.3599 0.07256 0.06697 -0.0664 0.0093 1.0002
15.000 1.3632 0.07512 0.06956 -0.0662 0.0086 1.0002
15.250 1.3674 0.07758 0.07206 -0.0661 0.0081 1.0002
15.500 1.3703 0.08025 0.07476 -0.0661 0.0075 1.0002
15.750 1.3738 0.08279 0.07734 -0.0660 0.0070 1.0002
16.000 1.3766 0.08546 0.08004 -0.0660 0.0066 1.0002
16.250 1.3792 0.08818 0.08281 -0.0661 0.0063 1.0002
16.500 1.3830 0.09075 0.08542 -0.0661 0.0060 1.0002
16.750 1.3856 0.09350 0.08822 -0.0662 0.0057 1.0002
17.000 1.3879 0.09628 0.09104 -0.0664 0.0055 1.0002
17.250 1.3909 0.09895 0.09376 -0.0665 0.0053 1.0002
17.500 1.3924 0.10186 0.09672 -0.0667 0.0050 1.0002
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