Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 50,000 Max Cl/Cd: 35.54 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg3-il-50000-n5.txt Download as CSV file: xf-fg3-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3590 0.10382 0.09777 -0.0290 1.0000 0.0999
-7.750 -0.3815 0.10319 0.09729 -0.0277 1.0000 0.1007
-7.500 -0.3995 0.10206 0.09625 -0.0280 1.0000 0.1012
-7.250 -0.3855 0.09685 0.09110 -0.0237 1.0000 0.1047
-7.000 -0.3877 0.09442 0.08873 -0.0215 1.0000 0.1095
-6.750 -0.4002 0.09256 0.08691 -0.0213 1.0000 0.1140
-6.500 -0.4180 0.09162 0.08598 -0.0239 1.0000 0.1165
-6.250 -0.4090 0.08710 0.08157 -0.0188 1.0000 0.1219
-6.000 -0.4123 0.08477 0.07926 -0.0181 1.0000 0.1281
-5.750 -0.4191 0.08228 0.07675 -0.0195 1.0000 0.1335
-5.500 -0.4151 0.07923 0.07377 -0.0161 1.0000 0.1412
-5.250 -0.4167 0.07643 0.07094 -0.0164 1.0000 0.1504
-4.750 -0.4104 0.07088 0.06538 -0.0139 1.0000 0.1685
-4.500 -0.3885 0.06739 0.06180 -0.0167 0.9937 0.1887
-4.250 -0.3678 0.06404 0.05841 -0.0183 0.9869 0.2179
-3.750 -0.2721 0.05214 0.04483 -0.0320 0.9696 0.0882
-3.500 -0.2359 0.04845 0.04038 -0.0334 0.9601 0.0723
-3.250 -0.2032 0.04563 0.03705 -0.0347 0.9500 0.0713
-3.000 -0.1690 0.04294 0.03383 -0.0360 0.9400 0.0715
-2.750 -0.1344 0.04002 0.03059 -0.0376 0.9306 0.0703
-2.500 -0.1027 0.03780 0.02796 -0.0381 0.9197 0.0695
-2.250 -0.0677 0.03635 0.02586 -0.0387 0.9094 0.0717
-2.000 -0.0269 0.03427 0.02343 -0.0407 0.9012 0.0725
-1.750 0.0062 0.03283 0.02164 -0.0411 0.8898 0.0723
-1.500 0.0431 0.03145 0.01998 -0.0423 0.8788 0.0726
-1.250 0.0867 0.02998 0.01833 -0.0448 0.8697 0.0747
-1.000 0.1327 0.02884 0.01703 -0.0478 0.8592 0.0794
-0.500 0.2127 0.02707 0.01487 -0.0511 0.8338 0.0829
-0.250 0.2480 0.02634 0.01397 -0.0518 0.8195 0.0852
0.000 0.2824 0.02562 0.01313 -0.0525 0.8039 0.0880
0.250 0.3169 0.02493 0.01237 -0.0532 0.7875 0.0931
0.500 0.3527 0.02425 0.01166 -0.0540 0.7702 0.1055
1.000 0.5085 0.02103 0.01039 -0.0734 0.7235 1.0000
1.250 0.5419 0.02080 0.00985 -0.0736 0.6948 1.0000
1.500 0.5742 0.02068 0.00943 -0.0738 0.6635 1.0000
1.750 0.6055 0.02067 0.00910 -0.0739 0.6309 1.0000
2.000 0.6350 0.02081 0.00890 -0.0738 0.6001 1.0000
2.250 0.6625 0.02107 0.00884 -0.0734 0.5730 1.0000
2.500 0.6881 0.02143 0.00893 -0.0729 0.5501 1.0000
2.750 0.7132 0.02185 0.00909 -0.0723 0.5307 1.0000
3.000 0.7373 0.02231 0.00936 -0.0716 0.5132 1.0000
3.250 0.7621 0.02278 0.00970 -0.0712 0.4986 1.0000
3.500 0.7873 0.02328 0.01004 -0.0708 0.4853 1.0000
3.750 0.8123 0.02379 0.01047 -0.0704 0.4732 1.0000
4.000 0.8370 0.02431 0.01098 -0.0700 0.4621 1.0000
4.250 0.8630 0.02484 0.01146 -0.0699 0.4525 1.0000
4.500 0.8889 0.02539 0.01199 -0.0698 0.4435 1.0000
4.750 0.9133 0.02597 0.01263 -0.0694 0.4349 1.0000
5.000 0.9398 0.02654 0.01318 -0.0694 0.4272 1.0000
5.250 0.9629 0.02719 0.01394 -0.0688 0.4196 1.0000
5.500 0.9886 0.02782 0.01461 -0.0687 0.4132 1.0000
5.750 1.0120 0.02853 0.01546 -0.0682 0.4068 1.0000
6.000 1.0348 0.02924 0.01629 -0.0676 0.4004 1.0000
6.250 1.0606 0.02993 0.01704 -0.0675 0.3950 1.0000
6.500 1.0792 0.03079 0.01814 -0.0663 0.3888 1.0000
6.750 1.1025 0.03159 0.01911 -0.0658 0.3839 1.0000
7.000 1.1260 0.03243 0.02010 -0.0654 0.3793 1.0000
7.250 1.1419 0.03345 0.02141 -0.0638 0.3738 1.0000
7.500 1.1633 0.03435 0.02249 -0.0631 0.3690 1.0000
7.750 1.1865 0.03527 0.02362 -0.0626 0.3648 1.0000
8.000 1.1980 0.03656 0.02527 -0.0605 0.3601 1.0000
8.250 1.2148 0.03769 0.02668 -0.0591 0.3556 1.0000
8.500 1.2379 0.03840 0.02755 -0.0585 0.3498 1.0000
8.750 1.2469 0.03875 0.02808 -0.0554 0.3375 1.0000
9.000 1.2532 0.03894 0.02847 -0.0518 0.3238 1.0000
9.250 1.2576 0.03925 0.02896 -0.0480 0.3111 1.0000
9.500 1.2593 0.03936 0.02922 -0.0438 0.2970 1.0000
9.750 1.2539 0.03946 0.02941 -0.0385 0.2807 1.0000
10.000 1.2441 0.03995 0.03003 -0.0329 0.2663 1.0000
10.250 1.2319 0.04065 0.03083 -0.0275 0.2486 1.0000
10.500 1.2245 0.04185 0.03220 -0.0235 0.2321 1.0000
10.750 1.2154 0.04368 0.03430 -0.0202 0.2098 1.0000
11.000 1.2063 0.04593 0.03669 -0.0177 0.1727 1.0000
11.500 1.1605 0.05394 0.04376 -0.0138 0.0768 1.0000
11.750 1.1374 0.05931 0.04908 -0.0137 0.0680 1.0000
12.000 1.1184 0.06477 0.05464 -0.0144 0.0643 1.0000
12.250 1.0983 0.07085 0.06082 -0.0158 0.0614 1.0000
12.500 1.0818 0.07671 0.06684 -0.0173 0.0598 1.0000
12.750 1.0656 0.08270 0.07295 -0.0190 0.0582 1.0000
13.000 1.0495 0.08873 0.07907 -0.0207 0.0562 1.0000
13.250 1.0357 0.09440 0.08480 -0.0223 0.0544 1.0000
13.500 1.0222 0.10001 0.09045 -0.0239 0.0523 1.0000
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Polar data table (+)
Polar graphs
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