Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 50,000 Max Cl/Cd: 37.75 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg2-il-50000-n5.txt Download as CSV file: xf-fg2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 2
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 -0.4042 0.09804 0.09146 -0.0212 1.0000 0.1045
-7.750 -0.4168 0.09635 0.08990 -0.0233 1.0000 0.1072
-7.500 -0.4272 0.09469 0.08831 -0.0277 1.0000 0.1083
-7.250 -0.4091 0.08927 0.08295 -0.0214 1.0000 0.1177
-7.000 -0.4196 0.08765 0.08138 -0.0263 1.0000 0.1228
-6.750 -0.4098 0.08309 0.07691 -0.0226 1.0000 0.1277
-6.500 -0.4118 0.08077 0.07460 -0.0249 1.0000 0.1371
-6.250 -0.4066 0.07692 0.07082 -0.0235 1.0000 0.1413
-6.000 -0.4069 0.07488 0.06870 -0.0261 1.0000 0.1534
-5.750 -0.3974 0.07072 0.06467 -0.0222 1.0000 0.1591
-5.500 -0.3934 0.06777 0.06172 -0.0218 1.0000 0.1726
-5.250 -0.3884 0.06503 0.05902 -0.0202 1.0000 0.1909
-4.750 -0.3820 0.05990 0.05396 -0.0157 1.0000 0.2468
-4.250 -0.3114 0.04813 0.04061 -0.0255 1.0000 0.0769
-4.000 -0.2975 0.04506 0.03738 -0.0242 1.0000 0.0731
-3.750 -0.2819 0.04247 0.03446 -0.0229 1.0000 0.0730
-3.500 -0.2655 0.04009 0.03174 -0.0214 1.0000 0.0733
-3.250 -0.2482 0.03778 0.02909 -0.0199 1.0000 0.0714
-3.000 -0.2296 0.03562 0.02648 -0.0183 1.0000 0.0692
-2.750 -0.2108 0.03382 0.02428 -0.0167 1.0000 0.0683
-2.500 -0.1879 0.03235 0.02252 -0.0162 0.9979 0.0714
-2.250 -0.1462 0.03061 0.02027 -0.0189 0.9881 0.0728
-2.000 -0.1042 0.02900 0.01823 -0.0214 0.9778 0.0723
-1.750 -0.0624 0.02760 0.01645 -0.0239 0.9659 0.0724
-1.500 -0.0199 0.02638 0.01493 -0.0264 0.9521 0.0737
-1.250 0.0250 0.02546 0.01368 -0.0293 0.9362 0.0786
-1.000 0.0748 0.02426 0.01232 -0.0331 0.9208 0.0808
-0.750 0.1207 0.02331 0.01121 -0.0361 0.9046 0.0827
-0.500 0.1645 0.02251 0.01028 -0.0388 0.8881 0.0855
-0.250 0.2073 0.02185 0.00947 -0.0412 0.8716 0.0894
0.000 0.2471 0.02132 0.00883 -0.0432 0.8523 0.0955
0.250 0.2870 0.02081 0.00834 -0.0452 0.8319 0.1095
0.750 0.4250 0.01805 0.00755 -0.0615 0.7902 1.0000
1.000 0.4628 0.01805 0.00727 -0.0630 0.7643 1.0000
1.250 0.4991 0.01810 0.00706 -0.0642 0.7391 1.0000
1.500 0.5308 0.01825 0.00701 -0.0645 0.7137 1.0000
1.750 0.5606 0.01847 0.00702 -0.0646 0.6900 1.0000
2.000 0.5891 0.01874 0.00710 -0.0644 0.6681 1.0000
2.250 0.6159 0.01907 0.00728 -0.0640 0.6472 1.0000
2.500 0.6424 0.01943 0.00754 -0.0636 0.6275 1.0000
2.750 0.6690 0.01982 0.00783 -0.0633 0.6093 1.0000
3.000 0.6954 0.02023 0.00816 -0.0629 0.5925 1.0000
3.250 0.7212 0.02066 0.00857 -0.0625 0.5765 1.0000
3.500 0.7465 0.02111 0.00901 -0.0620 0.5612 1.0000
3.750 0.7721 0.02157 0.00948 -0.0616 0.5470 1.0000
4.000 0.7969 0.02206 0.01004 -0.0610 0.5335 1.0000
4.250 0.8208 0.02256 0.01061 -0.0603 0.5201 1.0000
4.500 0.8437 0.02302 0.01112 -0.0594 0.5053 1.0000
4.750 0.8654 0.02343 0.01154 -0.0581 0.4888 1.0000
5.000 0.8849 0.02382 0.01203 -0.0564 0.4706 1.0000
5.250 0.9045 0.02422 0.01251 -0.0548 0.4533 1.0000
5.500 0.9253 0.02467 0.01306 -0.0534 0.4386 1.0000
5.750 0.9464 0.02515 0.01366 -0.0522 0.4248 1.0000
6.000 0.9672 0.02565 0.01433 -0.0509 0.4112 1.0000
6.250 0.9876 0.02616 0.01498 -0.0495 0.3973 1.0000
6.500 1.0077 0.02670 0.01567 -0.0481 0.3832 1.0000
6.750 1.0277 0.02728 0.01641 -0.0466 0.3693 1.0000
7.000 1.0476 0.02792 0.01727 -0.0452 0.3555 1.0000
7.250 1.0668 0.02862 0.01816 -0.0437 0.3410 1.0000
7.500 1.0836 0.02933 0.01909 -0.0418 0.3243 1.0000
7.750 1.0930 0.02969 0.01951 -0.0386 0.2989 1.0000
8.000 1.1002 0.03017 0.02012 -0.0353 0.2710 1.0000
8.250 1.1125 0.03088 0.02104 -0.0329 0.2509 1.0000
8.500 1.1240 0.03162 0.02210 -0.0304 0.2300 1.0000
8.750 1.1264 0.03245 0.02282 -0.0268 0.1925 1.0000
9.000 1.1225 0.03404 0.02402 -0.0230 0.1506 1.0000
9.250 1.1202 0.03593 0.02581 -0.0195 0.1169 1.0000
9.500 1.1162 0.03801 0.02785 -0.0159 0.0778 1.0000
9.750 1.1060 0.04062 0.03020 -0.0125 0.0614 1.0000
10.000 1.0967 0.04338 0.03291 -0.0097 0.0537 1.0000
10.250 1.0866 0.04644 0.03597 -0.0076 0.0493 1.0000
10.500 1.0801 0.04947 0.03917 -0.0064 0.0461 1.0000
10.750 1.0713 0.05302 0.04287 -0.0057 0.0433 1.0000
11.000 1.0625 0.05687 0.04685 -0.0057 0.0416 1.0000
11.250 1.0551 0.06080 0.05091 -0.0061 0.0406 1.0000
11.500 1.0480 0.06487 0.05507 -0.0066 0.0395 1.0000
11.750 1.0441 0.06860 0.05901 -0.0070 0.0383 1.0000
12.000 1.0409 0.07231 0.06289 -0.0073 0.0374 1.0000
12.250 1.0373 0.07616 0.06692 -0.0077 0.0360 1.0000
12.500 1.0336 0.08009 0.07100 -0.0083 0.0348 1.0000
12.750 1.0308 0.08393 0.07498 -0.0089 0.0339 1.0000
13.000 1.0259 0.08809 0.07925 -0.0099 0.0326 1.0000
13.250 1.0230 0.09195 0.08315 -0.0104 0.0318 1.0000
13.500 1.0186 0.09658 0.08805 -0.0116 0.0309 1.0000
13.750 1.0138 0.10134 0.09304 -0.0130 0.0305 1.0000
14.000 1.0068 0.10674 0.09867 -0.0149 0.0301 1.0000
14.250 0.9995 0.11235 0.10448 -0.0171 0.0301 1.0000
14.500 0.9894 0.11878 0.11112 -0.0199 0.0301 1.0000
14.750 0.9779 0.12588 0.11839 -0.0233 0.0302 1.0000
15.000 0.9653 0.13359 0.12625 -0.0272 0.0304 1.0000
15.250 0.9525 0.14182 0.13459 -0.0313 0.0307 1.0000
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Polar data table (+)
Polar graphs
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