WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 50,000 Max Cl/Cd: 12.31 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66a175-il-50000-n5.txt Download as CSV file: xf-fx66a175-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2682 0.11719 0.11131 -0.0523 1.0000 0.0439
-11.250 -0.2685 0.11315 0.10741 -0.0537 1.0000 0.0433
-11.000 -0.2704 0.10900 0.10340 -0.0552 1.0000 0.0426
-10.750 -0.2601 0.10232 0.09677 -0.0614 0.9279 0.0419
-10.250 -0.2464 0.08591 0.08017 -0.0783 0.8615 0.0401
-10.000 -0.2575 0.07686 0.07095 -0.0871 0.8397 0.0390
-9.750 -0.2838 0.06836 0.06215 -0.0956 0.8203 0.0376
-9.500 -0.3040 0.06275 0.05619 -0.1008 0.8016 0.0371
-9.250 -0.3188 0.05915 0.05226 -0.1028 0.7854 0.0368
-9.000 -0.3259 0.05598 0.04874 -0.1035 0.7723 0.0367
-8.750 -0.3265 0.05304 0.04550 -0.1037 0.7606 0.0371
-8.500 -0.3216 0.05050 0.04269 -0.1038 0.7502 0.0381
-8.250 -0.3127 0.04819 0.04009 -0.1036 0.7413 0.0393
-8.000 -0.3025 0.04598 0.03758 -0.1033 0.7321 0.0411
-7.750 -0.2891 0.04373 0.03488 -0.1029 0.7241 0.0428
-7.500 -0.2720 0.04153 0.03226 -0.1023 0.7164 0.0444
-7.250 -0.2508 0.03955 0.02988 -0.1015 0.7093 0.0457
-7.000 -0.2262 0.03793 0.02787 -0.1005 0.7023 0.0474
-6.750 -0.2035 0.03650 0.02647 -0.0995 0.6959 0.0512
-6.500 -0.1823 0.03550 0.02532 -0.0984 0.6894 0.0564
-6.250 -0.1610 0.03452 0.02411 -0.0969 0.6841 0.0612
-6.000 -0.1461 0.03354 0.02318 -0.0954 0.6775 0.0663
-5.750 -0.1302 0.03253 0.02204 -0.0942 0.6721 0.0761
-5.500 -0.1159 0.03139 0.02093 -0.0933 0.6667 0.0904
-5.250 -0.1032 0.02993 0.01968 -0.0928 0.6611 0.1191
-5.000 -0.0951 0.02743 0.01824 -0.0926 0.6570 0.2471
-4.750 -0.0782 0.02883 0.02027 -0.0891 0.6516 0.4423
-4.500 -0.0577 0.03051 0.02170 -0.0863 0.6463 0.5039
-4.250 -0.0359 0.03210 0.02317 -0.0822 0.6421 0.5406
-4.000 -0.0160 0.03261 0.02345 -0.0802 0.6372 0.5632
-3.750 0.0054 0.03282 0.02344 -0.0788 0.6324 0.5780
-3.500 0.0293 0.03280 0.02314 -0.0780 0.6285 0.5894
-3.250 0.0521 0.03279 0.02292 -0.0772 0.6244 0.5978
-3.000 0.0732 0.03274 0.02266 -0.0770 0.6197 0.6070
-2.750 0.0966 0.03273 0.02244 -0.0763 0.6160 0.6136
-2.500 0.1227 0.03257 0.02198 -0.0769 0.6131 0.6211
-2.250 0.1435 0.03269 0.02200 -0.0763 0.6091 0.6257
-2.000 0.1650 0.03281 0.02197 -0.0761 0.6048 0.6314
-1.750 0.1895 0.03282 0.02176 -0.0763 0.6013 0.6368
-1.500 0.2156 0.03279 0.02154 -0.0763 0.5985 0.6413
-1.250 0.2357 0.03311 0.02177 -0.0762 0.5942 0.6458
-1.000 0.2573 0.03341 0.02194 -0.0764 0.5902 0.6503
-0.750 0.2805 0.03362 0.02202 -0.0762 0.5871 0.6538
-0.500 0.3064 0.03377 0.02202 -0.0764 0.5847 0.6578
-0.250 0.3283 0.03420 0.02234 -0.0765 0.5817 0.6616
0.000 0.3431 0.03501 0.02313 -0.0760 0.5773 0.6654
0.250 0.3638 0.03549 0.02355 -0.0757 0.5739 0.6691
0.500 0.3892 0.03578 0.02374 -0.0759 0.5712 0.6732
0.750 0.4176 0.03600 0.02380 -0.0766 0.5691 0.6776
1.000 0.4218 0.03753 0.02541 -0.0751 0.5639 0.6811
1.250 0.4362 0.03852 0.02640 -0.0744 0.5602 0.6850
1.500 0.4587 0.03910 0.02692 -0.0745 0.5574 0.6897
1.750 0.4859 0.03946 0.02719 -0.0749 0.5553 0.6946
2.000 0.4835 0.04149 0.02931 -0.0730 0.5499 0.6985
2.250 0.4913 0.04301 0.03085 -0.0720 0.5455 0.7033
2.500 0.5122 0.04381 0.03161 -0.0721 0.5428 0.7088
2.750 0.5385 0.04420 0.03199 -0.0723 0.5408 0.7141
3.000 0.5090 0.04806 0.03597 -0.0690 0.5332 0.7184
3.250 0.5186 0.04965 0.03757 -0.0685 0.5298 0.7243
3.500 0.5407 0.05041 0.03835 -0.0685 0.5275 0.7308
3.750 0.5691 0.05083 0.03877 -0.0689 0.5259 0.7387
4.000 0.5297 0.05605 0.04412 -0.0668 0.5170 0.7441
4.250 0.5459 0.05742 0.04553 -0.0668 0.5145 0.7531
4.500 0.5665 0.05842 0.04661 -0.0669 0.5126 0.7633
4.750 0.5641 0.06107 0.04938 -0.0663 0.5082 0.7739
5.000 0.5638 0.06347 0.05190 -0.0658 0.5034 0.7881
5.250 0.5790 0.06479 0.05339 -0.0656 0.5005 0.8124
5.500 0.5989 0.06569 0.05456 -0.0660 0.4983 0.9818
5.750 0.6236 0.06678 0.05558 -0.0665 0.4967 1.0000
6.000 0.6043 0.07078 0.05958 -0.0661 0.4899 1.0000
6.250 0.6194 0.07257 0.06138 -0.0666 0.4866 1.0000
6.500 0.6412 0.07394 0.06272 -0.0671 0.4841 1.0000
6.750 0.6575 0.07564 0.06441 -0.0674 0.4811 1.0000
7.000 0.6503 0.07879 0.06758 -0.0672 0.4753 1.0000
7.250 0.6654 0.08056 0.06936 -0.0674 0.4720 1.0000
7.500 0.6883 0.08181 0.07064 -0.0677 0.4694 1.0000
7.750 0.6884 0.08455 0.07342 -0.0676 0.4646 1.0000
8.000 0.6931 0.08701 0.07592 -0.0677 0.4602 1.0000
8.250 0.7110 0.08858 0.07753 -0.0678 0.4568 1.0000
8.500 0.7363 0.08971 0.07871 -0.0680 0.4544 1.0000
8.750 0.7244 0.09324 0.08233 -0.0679 0.4478 1.0000
9.000 0.7383 0.09509 0.08425 -0.0680 0.4437 1.0000
9.250 0.7622 0.09627 0.08551 -0.0681 0.4407 1.0000
9.500 0.7565 0.09937 0.08868 -0.0681 0.4338 1.0000
9.750 0.7703 0.10119 0.09059 -0.0682 0.4291 1.0000
10.000 0.7952 0.10229 0.09182 -0.0682 0.4261 1.0000
10.250 0.7870 0.10559 0.09521 -0.0683 0.4184 1.0000
10.500 0.8045 0.10718 0.09691 -0.0684 0.4140 1.0000
10.750 0.8193 0.10903 0.09887 -0.0685 0.4098 1.0000
11.000 0.8175 0.11192 0.10187 -0.0687 0.4025 1.0000
11.250 0.8404 0.11315 0.10325 -0.0687 0.3988 1.0000
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Polar data table (+)
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