Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 100,000 Max Cl/Cd: 48.77 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg3-il-100000.txt Download as CSV file: xf-fg3-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 3
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3830 0.09419 0.08998 -0.0229 1.0000 0.0644
-7.250 -0.4020 0.09294 0.08880 -0.0216 1.0000 0.0656
-7.000 -0.4174 0.09144 0.08734 -0.0228 1.0000 0.0666
-6.750 -0.4283 0.08992 0.08575 -0.0244 1.0000 0.0672
-6.500 -0.4346 0.08827 0.08396 -0.0249 1.0000 0.0675
-6.250 -0.4305 0.08188 0.07785 -0.0198 1.0000 0.0695
-6.000 -0.4296 0.07919 0.07521 -0.0171 1.0000 0.0716
-5.750 -0.4294 0.07658 0.07259 -0.0159 1.0000 0.0742
-5.500 -0.4278 0.07388 0.06984 -0.0158 1.0000 0.0774
-5.250 -0.4215 0.07360 0.06901 -0.0195 1.0000 0.0819
-5.000 -0.4197 0.06759 0.06327 -0.0173 1.0000 0.0837
-4.750 -0.4152 0.06482 0.06056 -0.0150 1.0000 0.0863
-4.500 -0.4079 0.06239 0.05806 -0.0139 1.0000 0.0917
-4.250 -0.3973 0.05962 0.05496 -0.0147 1.0000 0.0986
-4.000 -0.3656 0.05719 0.05220 -0.0183 0.9937 0.1129
-3.750 -0.3325 0.05312 0.04809 -0.0220 0.9852 0.1289
-3.500 -0.3027 0.04972 0.04464 -0.0244 0.9761 0.1455
-3.250 -0.2733 0.04693 0.04179 -0.0262 0.9668 0.1654
-3.000 -0.2438 0.04436 0.03911 -0.0280 0.9573 0.1959
-2.500 -0.1945 0.04043 0.03519 -0.0284 0.9380 0.3102
-2.250 -0.1751 0.03843 0.03329 -0.0265 0.9274 0.3724
-2.000 -0.1520 0.03575 0.03082 -0.0244 0.9188 0.4324
-1.750 -0.1276 0.03318 0.02841 -0.0222 0.9095 0.4862
-1.500 -0.0098 0.03043 0.02241 -0.0363 0.9003 0.1404
-1.250 0.0465 0.02827 0.01958 -0.0391 0.8938 0.1098
-1.000 0.0853 0.02661 0.01764 -0.0399 0.8825 0.1011
-0.750 0.1295 0.02527 0.01610 -0.0419 0.8720 0.1006
-0.500 0.1869 0.02394 0.01454 -0.0460 0.8651 0.0972
-0.250 0.2292 0.02256 0.01317 -0.0478 0.8531 0.0965
0.000 0.2746 0.02118 0.01185 -0.0500 0.8414 0.0971
0.250 0.3236 0.01975 0.01049 -0.0531 0.8300 0.1014
0.500 0.3684 0.01873 0.00941 -0.0553 0.8138 0.1112
0.750 0.5850 0.01478 0.00751 -0.0934 0.7910 1.0000
1.000 0.6176 0.01435 0.00682 -0.0933 0.7483 1.0000
1.250 0.6516 0.01414 0.00621 -0.0935 0.6939 1.0000
1.500 0.6805 0.01431 0.00590 -0.0931 0.6399 1.0000
1.750 0.7050 0.01470 0.00585 -0.0921 0.5981 1.0000
2.000 0.7283 0.01516 0.00595 -0.0911 0.5679 1.0000
2.250 0.7513 0.01563 0.00617 -0.0901 0.5442 1.0000
2.500 0.7756 0.01612 0.00643 -0.0894 0.5255 1.0000
2.750 0.7999 0.01662 0.00672 -0.0888 0.5097 1.0000
3.000 0.8236 0.01710 0.00707 -0.0881 0.4956 1.0000
3.250 0.8472 0.01758 0.00746 -0.0874 0.4832 1.0000
3.500 0.8715 0.01809 0.00792 -0.0868 0.4729 1.0000
3.750 0.8981 0.01865 0.00833 -0.0867 0.4638 1.0000
4.000 0.9199 0.01914 0.00887 -0.0857 0.4546 1.0000
4.250 0.9452 0.01971 0.00937 -0.0854 0.4466 1.0000
4.500 0.9676 0.02023 0.00996 -0.0845 0.4385 1.0000
4.750 0.9929 0.02085 0.01054 -0.0843 0.4319 1.0000
5.000 1.0146 0.02142 0.01123 -0.0833 0.4252 1.0000
5.250 1.0406 0.02207 0.01184 -0.0832 0.4198 1.0000
5.500 1.0614 0.02274 0.01270 -0.0821 0.4140 1.0000
5.750 1.0839 0.02337 0.01342 -0.0813 0.4082 1.0000
6.000 1.1102 0.02412 0.01415 -0.0813 0.4033 1.0000
6.250 1.1278 0.02487 0.01516 -0.0796 0.3982 1.0000
6.500 1.1495 0.02563 0.01609 -0.0787 0.3935 1.0000
6.750 1.1751 0.02643 0.01693 -0.0786 0.3893 1.0000
7.000 1.1904 0.02723 0.01801 -0.0766 0.3832 1.0000
7.250 1.2155 0.02755 0.01825 -0.0761 0.3740 1.0000
7.500 1.2294 0.02765 0.01851 -0.0735 0.3616 1.0000
7.750 1.2447 0.02788 0.01885 -0.0713 0.3505 1.0000
8.000 1.2623 0.02792 0.01894 -0.0694 0.3391 1.0000
8.250 1.2765 0.02766 0.01870 -0.0667 0.3251 1.0000
8.500 1.2841 0.02723 0.01833 -0.0628 0.3086 1.0000
8.750 1.2895 0.02690 0.01814 -0.0584 0.2928 1.0000
9.000 1.2874 0.02644 0.01778 -0.0526 0.2729 1.0000
9.250 1.2813 0.02627 0.01774 -0.0462 0.2467 1.0000
9.500 1.2757 0.02650 0.01794 -0.0402 0.2115 1.0000
9.750 1.2583 0.02822 0.01895 -0.0335 0.1150 1.0000
10.000 1.2404 0.03107 0.02131 -0.0279 0.0692 1.0000
10.250 1.2339 0.03318 0.02340 -0.0238 0.0618 1.0000
10.500 1.2296 0.03517 0.02556 -0.0203 0.0579 1.0000
10.750 1.2212 0.03754 0.02810 -0.0169 0.0550 1.0000
11.000 1.2138 0.03993 0.03067 -0.0141 0.0538 1.0000
11.250 1.1984 0.04318 0.03408 -0.0114 0.0521 1.0000
11.500 1.1855 0.04651 0.03756 -0.0096 0.0513 1.0000
11.750 1.1752 0.04995 0.04118 -0.0085 0.0499 1.0000
12.000 1.1658 0.05356 0.04495 -0.0080 0.0494 1.0000
12.250 1.1556 0.05755 0.04913 -0.0079 0.0479 1.0000
12.500 1.1482 0.06130 0.05301 -0.0079 0.0471 1.0000
12.750 1.1438 0.06466 0.05645 -0.0076 0.0460 1.0000
13.000 1.1458 0.06695 0.05878 -0.0065 0.0447 1.0000
13.250 1.1603 0.06738 0.05913 -0.0038 0.0433 1.0000
13.500 1.2534 0.06334 0.05466 0.0029 0.0405 1.0000
13.750 1.2614 0.06584 0.05738 0.0039 0.0401 1.0000
14.000 1.2594 0.06874 0.06054 0.0047 0.0396 1.0000
14.250 1.2607 0.07195 0.06401 0.0054 0.0391 1.0000
14.500 1.2689 0.07530 0.06758 0.0062 0.0395 1.0000
14.750 1.2682 0.07927 0.07180 0.0067 0.0397 1.0000
15.000 1.2657 0.08371 0.07648 0.0069 0.0401 1.0000
15.250 1.2679 0.08894 0.08195 0.0072 0.0406 1.0000
15.500 1.2537 0.09224 0.08546 0.0066 0.0410 1.0000
15.750 1.2357 0.09648 0.08992 0.0052 0.0413 1.0000
16.000 1.2148 0.10162 0.09531 0.0031 0.0416 1.0000
16.250 1.1914 0.10757 0.10151 0.0000 0.0420 1.0000
16.500 1.1664 0.11464 0.10884 -0.0040 0.0425 1.0000
16.750 1.1370 0.12301 0.11745 -0.0094 0.0430 1.0000
17.000 1.1033 0.13306 0.12773 -0.0161 0.0435 1.0000
17.250 1.0624 0.14600 0.14087 -0.0249 0.0443 1.0000
17.500 1.0077 0.16491 0.15988 -0.0372 0.0463 1.0000
17.750 0.9848 0.17726 0.17222 -0.0435 0.0495 1.0000
18.000 0.9809 0.18388 0.17882 -0.0460 0.0507 1.0000
18.250 0.9675 0.19926 0.19416 -0.0521 0.0625 1.0000
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Polar data table (+)
Polar graphs
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