FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il) Reynolds number: 500,000 Max Cl/Cd: 113.93 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s171-il-500000.txt Download as CSV file: xf-fx66s171-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-171 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4244 0.09427 0.09209 -0.0534 1.0000 0.0151
-12.750 -0.4702 0.07971 0.07745 -0.0618 1.0000 0.0146
-12.500 -0.5068 0.06903 0.06662 -0.0692 1.0000 0.0144
-12.250 -0.5374 0.06098 0.05845 -0.0746 1.0000 0.0141
-12.000 -0.5457 0.04825 0.04525 -0.0935 0.9330 0.0137
-11.750 -0.5268 0.03867 0.03483 -0.1125 0.8532 0.0137
-11.500 -0.5412 0.03551 0.03120 -0.1122 0.8009 0.0136
-11.250 -0.5502 0.03320 0.02857 -0.1112 0.7708 0.0137
-11.000 -0.5581 0.03110 0.02619 -0.1094 0.7495 0.0137
-10.750 -0.5601 0.02991 0.02478 -0.1069 0.7325 0.0140
-10.500 -0.5581 0.02835 0.02295 -0.1047 0.7190 0.0142
-10.250 -0.5497 0.02699 0.02135 -0.1031 0.7073 0.0145
-10.000 -0.5379 0.02573 0.01985 -0.1017 0.6966 0.0148
-9.750 -0.5232 0.02461 0.01852 -0.1005 0.6870 0.0151
-9.500 -0.5066 0.02363 0.01732 -0.0995 0.6785 0.0152
-9.250 -0.4928 0.02148 0.01503 -0.0982 0.6707 0.0157
-9.000 -0.4752 0.02048 0.01392 -0.0973 0.6635 0.0161
-8.750 -0.4555 0.01969 0.01308 -0.0965 0.6562 0.0167
-8.500 -0.4352 0.01902 0.01230 -0.0957 0.6497 0.0173
-8.250 -0.4142 0.01833 0.01152 -0.0950 0.6435 0.0180
-8.000 -0.3925 0.01772 0.01080 -0.0943 0.6374 0.0189
-7.750 -0.3698 0.01725 0.01020 -0.0938 0.6320 0.0195
-7.500 -0.3519 0.01610 0.00902 -0.0928 0.6267 0.0209
-7.250 -0.3280 0.01571 0.00858 -0.0924 0.6215 0.0228
-7.000 -0.3035 0.01537 0.00813 -0.0921 0.6168 0.0245
-6.750 -0.2818 0.01456 0.00730 -0.0915 0.6121 0.0272
-6.500 -0.2566 0.01421 0.00689 -0.0913 0.6074 0.0300
-6.250 -0.2327 0.01370 0.00628 -0.0909 0.6032 0.0334
-6.000 -0.2069 0.01336 0.00591 -0.0908 0.5992 0.0376
-5.750 -0.1815 0.01291 0.00544 -0.0906 0.5953 0.0436
-5.500 -0.1556 0.01255 0.00506 -0.0904 0.5916 0.0530
-5.250 -0.1300 0.01215 0.00468 -0.0903 0.5883 0.0720
-5.000 -0.1052 0.01156 0.00429 -0.0902 0.5851 0.1195
-4.750 -0.0811 0.01079 0.00387 -0.0902 0.5818 0.2064
-4.500 -0.0571 0.01005 0.00355 -0.0901 0.5784 0.3230
-4.250 -0.0304 0.00980 0.00343 -0.0901 0.5751 0.3766
-4.000 -0.0027 0.00978 0.00342 -0.0902 0.5720 0.4096
-3.750 0.0258 0.00978 0.00341 -0.0903 0.5691 0.4323
-3.500 0.0542 0.00980 0.00341 -0.0904 0.5661 0.4499
-3.250 0.0828 0.00985 0.00343 -0.0905 0.5633 0.4644
-3.000 0.1116 0.00993 0.00343 -0.0906 0.5607 0.4763
-2.750 0.1400 0.01001 0.00345 -0.0907 0.5580 0.4857
-2.500 0.1685 0.01012 0.00351 -0.0909 0.5554 0.4968
-2.250 0.1972 0.01019 0.00354 -0.0910 0.5530 0.5068
-2.000 0.2255 0.01020 0.00356 -0.0911 0.5506 0.5142
-1.500 0.2827 0.01027 0.00358 -0.0914 0.5460 0.5278
-1.250 0.3114 0.01032 0.00357 -0.0916 0.5439 0.5325
-1.000 0.3404 0.01042 0.00358 -0.0919 0.5417 0.5368
-0.750 0.3689 0.01042 0.00359 -0.0921 0.5397 0.5406
-0.500 0.3973 0.01041 0.00360 -0.0923 0.5373 0.5444
-0.250 0.4258 0.01043 0.00360 -0.0924 0.5347 0.5486
0.000 0.4544 0.01047 0.00359 -0.0927 0.5322 0.5526
0.250 0.4828 0.01046 0.00358 -0.0928 0.5299 0.5563
0.500 0.5114 0.01053 0.00362 -0.0931 0.5277 0.5602
0.750 0.5400 0.01063 0.00370 -0.0933 0.5255 0.5646
1.000 0.5683 0.01066 0.00374 -0.0935 0.5234 0.5689
1.250 0.5964 0.01066 0.00379 -0.0937 0.5211 0.5730
1.500 0.6247 0.01070 0.00385 -0.0938 0.5189 0.5772
1.750 0.6531 0.01076 0.00389 -0.0941 0.5167 0.5817
2.000 0.6815 0.01081 0.00394 -0.0943 0.5146 0.5860
2.250 0.7099 0.01091 0.00405 -0.0945 0.5123 0.5907
2.500 0.7382 0.01103 0.00418 -0.0948 0.5103 0.5960
2.750 0.7660 0.01107 0.00428 -0.0949 0.5083 0.6012
3.000 0.7937 0.01111 0.00440 -0.0950 0.5061 0.6070
3.250 0.8217 0.01119 0.00450 -0.0951 0.5038 0.6138
3.500 0.8495 0.01124 0.00460 -0.0953 0.5016 0.6202
3.750 0.8777 0.01132 0.00471 -0.0955 0.4995 0.6276
4.000 0.9058 0.01144 0.00484 -0.0957 0.4973 0.6349
4.250 0.9336 0.01159 0.00503 -0.0959 0.4950 0.6442
4.500 0.9602 0.01160 0.00518 -0.0958 0.4926 0.6540
4.750 0.9872 0.01165 0.00532 -0.0958 0.4900 0.6651
5.000 1.0144 0.01170 0.00545 -0.0959 0.4874 0.6779
5.250 1.0417 0.01173 0.00557 -0.0959 0.4848 0.6933
5.500 1.0689 0.01180 0.00571 -0.0960 0.4822 0.7126
5.750 1.0951 0.01189 0.00593 -0.0958 0.4796 0.7393
6.000 1.1196 0.01185 0.00612 -0.0953 0.4768 0.7785
6.250 1.1415 0.01173 0.00630 -0.0941 0.4741 0.8521
6.500 1.1762 0.01165 0.00641 -0.0956 0.4713 1.0000
6.750 1.2036 0.01177 0.00655 -0.0958 0.4687 1.0000
7.000 1.2314 0.01201 0.00676 -0.0960 0.4658 1.0000
7.250 1.2562 0.01211 0.00697 -0.0957 0.4628 1.0000
7.500 1.2819 0.01224 0.00717 -0.0955 0.4596 1.0000
7.750 1.3080 0.01235 0.00733 -0.0954 0.4562 1.0000
8.000 1.3344 0.01246 0.00740 -0.0953 0.4513 1.0000
8.250 1.3545 0.01232 0.00739 -0.0940 0.4424 1.0000
8.500 1.3751 0.01226 0.00735 -0.0928 0.4310 1.0000
8.750 1.3956 0.01229 0.00740 -0.0916 0.4183 1.0000
9.000 1.4161 0.01243 0.00755 -0.0905 0.4063 1.0000
9.250 1.4357 0.01265 0.00779 -0.0893 0.3939 1.0000
9.500 1.4536 0.01296 0.00810 -0.0878 0.3802 1.0000
9.750 1.4681 0.01339 0.00850 -0.0858 0.3637 1.0000
10.000 1.4772 0.01391 0.00899 -0.0828 0.3417 1.0000
10.250 1.4774 0.01471 0.00968 -0.0785 0.3195 1.0000
10.500 1.4731 0.01577 0.01063 -0.0738 0.2927 1.0000
10.750 1.4623 0.01726 0.01197 -0.0688 0.2603 1.0000
11.000 1.4435 0.01944 0.01399 -0.0638 0.2268 1.0000
11.250 1.4196 0.02247 0.01687 -0.0595 0.1956 1.0000
11.500 1.3998 0.02581 0.02011 -0.0566 0.1691 1.0000
11.750 1.3786 0.02965 0.02385 -0.0543 0.1443 1.0000
12.000 1.3583 0.03364 0.02776 -0.0525 0.1213 1.0000
12.250 1.3392 0.03768 0.03171 -0.0510 0.1009 1.0000
12.500 1.3203 0.04183 0.03578 -0.0497 0.0799 1.0000
12.750 1.3030 0.04600 0.03986 -0.0487 0.0616 1.0000
13.000 1.2887 0.05005 0.04385 -0.0481 0.0459 1.0000
13.250 1.2777 0.05396 0.04771 -0.0477 0.0348 1.0000
13.500 1.2695 0.05770 0.05144 -0.0474 0.0272 1.0000
13.750 1.2665 0.06095 0.05473 -0.0473 0.0237 1.0000
14.000 1.2623 0.06445 0.05826 -0.0473 0.0207 1.0000
14.250 1.2631 0.06739 0.06127 -0.0474 0.0191 1.0000
14.500 1.2593 0.07096 0.06489 -0.0477 0.0174 1.0000
14.750 1.2566 0.07448 0.06847 -0.0479 0.0161 1.0000
15.000 1.2585 0.07747 0.07154 -0.0483 0.0151 1.0000
15.250 1.2583 0.08077 0.07491 -0.0487 0.0143 1.0000
15.500 1.2554 0.08448 0.07866 -0.0493 0.0133 1.0000
15.750 1.2492 0.08872 0.08298 -0.0500 0.0128 1.0000
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