Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 100,000 Max Cl/Cd: 53.62 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg2-il-100000-n5.txt Download as CSV file: xf-fg2-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3955 0.09236 0.08762 -0.0224 1.0000 0.0372
-7.750 -0.4017 0.08983 0.08516 -0.0227 1.0000 0.0376
-7.500 -0.4050 0.08689 0.08229 -0.0246 1.0000 0.0382
-7.250 -0.4057 0.08389 0.07932 -0.0292 1.0000 0.0390
-7.000 -0.4024 0.08069 0.07605 -0.0311 1.0000 0.0392
-6.750 -0.3985 0.07746 0.07272 -0.0322 1.0000 0.0394
-6.500 -0.3988 0.07229 0.06774 -0.0294 1.0000 0.0405
-6.250 -0.3947 0.06924 0.06471 -0.0277 1.0000 0.0415
-6.000 -0.3898 0.06630 0.06178 -0.0267 1.0000 0.0430
-5.750 -0.3833 0.06325 0.05869 -0.0264 1.0000 0.0446
-5.500 -0.3752 0.06010 0.05545 -0.0263 1.0000 0.0469
-5.250 -0.3602 0.05743 0.05225 -0.0279 1.0000 0.0517
-5.000 -0.3571 0.05355 0.04864 -0.0258 1.0000 0.0542
-4.750 -0.3469 0.05147 0.04649 -0.0245 1.0000 0.0614
-4.500 -0.3290 0.04795 0.04276 -0.0254 0.9979 0.0682
-4.250 -0.2942 0.04494 0.03923 -0.0288 0.9910 0.0803
-4.000 -0.2537 0.04014 0.03362 -0.0296 0.9850 0.0512
-3.750 -0.2263 0.03579 0.02918 -0.0311 0.9787 0.0495
-3.500 -0.1975 0.03246 0.02552 -0.0318 0.9710 0.0467
-3.250 -0.1665 0.02981 0.02242 -0.0323 0.9627 0.0461
-3.000 -0.1328 0.02776 0.01987 -0.0331 0.9542 0.0486
-2.750 -0.0996 0.02564 0.01735 -0.0338 0.9439 0.0481
-2.500 -0.0650 0.02387 0.01517 -0.0345 0.9316 0.0484
-2.250 -0.0275 0.02270 0.01359 -0.0356 0.9182 0.0508
-2.000 0.0094 0.02122 0.01185 -0.0369 0.9054 0.0508
-1.750 0.0467 0.01993 0.01036 -0.0382 0.8934 0.0508
-1.500 0.0845 0.01886 0.00915 -0.0398 0.8807 0.0511
-1.250 0.1219 0.01790 0.00813 -0.0414 0.8659 0.0516
-1.000 0.1580 0.01686 0.00712 -0.0429 0.8485 0.0545
-0.750 0.1951 0.01621 0.00645 -0.0446 0.8284 0.0577
-0.500 0.2300 0.01568 0.00582 -0.0457 0.8036 0.0583
-0.250 0.2679 0.01528 0.00525 -0.0474 0.7764 0.0591
0.000 0.3061 0.01500 0.00475 -0.0492 0.7471 0.0605
0.250 0.3424 0.01486 0.00437 -0.0506 0.7177 0.0624
0.750 0.4098 0.01478 0.00394 -0.0526 0.6663 0.0747
1.000 0.5363 0.01283 0.00406 -0.0747 0.6311 1.0000
1.250 0.5617 0.01306 0.00408 -0.0741 0.6103 1.0000
1.500 0.5867 0.01330 0.00413 -0.0734 0.5919 1.0000
1.750 0.6109 0.01353 0.00423 -0.0726 0.5744 1.0000
2.000 0.6349 0.01377 0.00435 -0.0717 0.5577 1.0000
2.250 0.6586 0.01402 0.00451 -0.0709 0.5415 1.0000
2.500 0.6821 0.01427 0.00468 -0.0699 0.5258 1.0000
2.750 0.7055 0.01453 0.00487 -0.0690 0.5109 1.0000
3.000 0.7286 0.01480 0.00510 -0.0680 0.4960 1.0000
3.250 0.7513 0.01507 0.00531 -0.0670 0.4805 1.0000
3.500 0.7734 0.01533 0.00553 -0.0658 0.4638 1.0000
3.750 0.7955 0.01560 0.00577 -0.0647 0.4478 1.0000
4.000 0.8174 0.01588 0.00602 -0.0635 0.4323 1.0000
4.250 0.8396 0.01616 0.00629 -0.0624 0.4182 1.0000
4.500 0.8615 0.01645 0.00658 -0.0612 0.4044 1.0000
4.750 0.8838 0.01676 0.00694 -0.0602 0.3926 1.0000
5.000 0.9062 0.01709 0.00731 -0.0592 0.3827 1.0000
5.250 0.9284 0.01743 0.00769 -0.0581 0.3728 1.0000
5.500 0.9506 0.01777 0.00813 -0.0571 0.3625 1.0000
5.750 0.9724 0.01814 0.00861 -0.0560 0.3525 1.0000
6.000 0.9937 0.01854 0.00906 -0.0548 0.3419 1.0000
6.250 1.0144 0.01892 0.00956 -0.0535 0.3289 1.0000
6.500 1.0327 0.01929 0.01000 -0.0518 0.3079 1.0000
6.750 1.0488 0.01967 0.01040 -0.0497 0.2754 1.0000
7.000 1.0665 0.02010 0.01086 -0.0480 0.2450 1.0000
7.250 1.0828 0.02067 0.01137 -0.0461 0.2072 1.0000
7.500 1.0977 0.02143 0.01202 -0.0440 0.1784 1.0000
7.750 1.1091 0.02254 0.01294 -0.0415 0.1451 1.0000
8.250 1.1216 0.02579 0.01549 -0.0354 0.0394 1.0000
8.500 1.1286 0.02725 0.01700 -0.0323 0.0298 1.0000
8.750 1.1361 0.02860 0.01844 -0.0292 0.0259 1.0000
9.000 1.1419 0.03001 0.01997 -0.0261 0.0236 1.0000
9.250 1.1468 0.03130 0.02147 -0.0228 0.0221 1.0000
9.500 1.1485 0.03267 0.02304 -0.0191 0.0211 1.0000
9.750 1.1484 0.03418 0.02474 -0.0154 0.0204 1.0000
10.000 1.1474 0.03582 0.02656 -0.0121 0.0199 1.0000
10.250 1.1449 0.03768 0.02860 -0.0090 0.0194 1.0000
10.500 1.1420 0.03971 0.03080 -0.0064 0.0190 1.0000
10.750 1.1368 0.04213 0.03337 -0.0043 0.0182 1.0000
11.000 1.1307 0.04487 0.03625 -0.0027 0.0174 1.0000
11.250 1.1266 0.04765 0.03921 -0.0016 0.0170 1.0000
11.500 1.1212 0.05081 0.04250 -0.0007 0.0164 1.0000
11.750 1.1171 0.05406 0.04587 0.0001 0.0158 1.0000
12.000 1.1174 0.05703 0.04898 0.0010 0.0156 1.0000
12.250 1.1178 0.06010 0.05219 0.0015 0.0153 1.0000
12.500 1.1174 0.06333 0.05561 0.0016 0.0152 1.0000
12.750 1.1161 0.06673 0.05920 0.0015 0.0152 1.0000
13.000 1.1125 0.07055 0.06323 0.0011 0.0151 1.0000
13.250 1.1071 0.07468 0.06757 0.0003 0.0150 1.0000
13.500 1.0989 0.07933 0.07243 -0.0010 0.0149 1.0000
13.750 1.0900 0.08421 0.07751 -0.0026 0.0149 1.0000
14.000 1.0789 0.08959 0.08310 -0.0048 0.0149 1.0000
14.250 1.0677 0.09510 0.08878 -0.0072 0.0149 1.0000
14.500 1.0545 0.10126 0.09513 -0.0102 0.0149 1.0000
14.750 1.0413 0.10768 0.10171 -0.0135 0.0150 1.0000
15.000 1.0265 0.11474 0.10894 -0.0172 0.0150 1.0000
15.250 1.0120 0.12211 0.11645 -0.0213 0.0151 1.0000
15.500 0.9963 0.13018 0.12467 -0.0258 0.0152 1.0000
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Polar data table (+)
Polar graphs
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