Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 100,000 Max Cl/Cd: 49.71 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg3-il-100000-n5.txt Download as CSV file: xf-fg3-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3680 0.10280 0.09848 -0.0310 1.0000 0.0349
-8.000 -0.3819 0.10121 0.09697 -0.0289 1.0000 0.0349
-7.750 -0.3939 0.09925 0.09506 -0.0280 1.0000 0.0350
-7.500 -0.3898 0.09561 0.09141 -0.0311 0.9974 0.0351
-7.250 -0.3800 0.09016 0.08601 -0.0313 0.9945 0.0357
-7.000 -0.3682 0.08630 0.08217 -0.0308 0.9913 0.0366
-6.750 -0.3532 0.08291 0.07876 -0.0325 0.9873 0.0402
-6.500 -0.3374 0.07858 0.07436 -0.0379 0.9804 0.0427
-6.250 -0.2535 0.05886 0.05486 -0.0487 0.9591 0.0483
-6.000 -0.2415 0.05486 0.05081 -0.0506 0.9539 0.0502
-5.750 -0.2898 0.06549 0.06097 -0.0495 0.9608 0.0478
-5.500 -0.2703 0.06204 0.05745 -0.0513 0.9564 0.0506
-5.250 -0.2453 0.06019 0.05488 -0.0549 0.9465 0.0580
-5.000 -0.2283 0.05432 0.04931 -0.0561 0.9433 0.0609
-4.750 -0.2039 0.05267 0.04709 -0.0574 0.9327 0.0722
-4.500 -0.1810 0.04794 0.04259 -0.0588 0.9250 0.0771
-4.250 -0.1480 0.04445 0.03868 -0.0614 0.9166 0.0890
-4.000 -0.1230 0.04150 0.03561 -0.0617 0.9068 0.0947
-3.750 -0.0844 0.03601 0.02926 -0.0617 0.9019 0.0538
-3.500 -0.0632 0.03293 0.02542 -0.0590 0.8933 0.0468
-3.250 -0.0315 0.03048 0.02257 -0.0595 0.8884 0.0470
-3.000 -0.0079 0.02879 0.02076 -0.0589 0.8807 0.0492
-2.750 0.0244 0.02686 0.01838 -0.0591 0.8748 0.0489
-2.500 0.0529 0.02533 0.01647 -0.0585 0.8672 0.0483
-2.250 0.0863 0.02401 0.01493 -0.0593 0.8602 0.0500
-2.000 0.1135 0.02302 0.01373 -0.0588 0.8509 0.0521
-1.750 0.1531 0.02172 0.01219 -0.0605 0.8440 0.0519
-1.500 0.1775 0.02089 0.01123 -0.0593 0.8324 0.0520
-1.250 0.2045 0.02008 0.01033 -0.0587 0.8204 0.0523
-1.000 0.2319 0.01934 0.00951 -0.0582 0.8082 0.0528
-0.750 0.2578 0.01872 0.00885 -0.0574 0.7936 0.0544
-0.500 0.2839 0.01819 0.00827 -0.0566 0.7775 0.0568
-0.250 0.3120 0.01761 0.00760 -0.0562 0.7594 0.0578
0.000 0.3425 0.01708 0.00696 -0.0563 0.7396 0.0584
0.250 0.3738 0.01663 0.00636 -0.0565 0.7143 0.0597
0.500 0.4087 0.01630 0.00581 -0.0576 0.6833 0.0617
0.750 0.4437 0.01613 0.00538 -0.0587 0.6446 0.0651
1.000 0.4760 0.01611 0.00506 -0.0593 0.6025 0.0706
1.500 0.6590 0.01499 0.00528 -0.0879 0.5005 1.0000
1.750 0.6799 0.01532 0.00538 -0.0865 0.4795 1.0000
2.000 0.7013 0.01565 0.00550 -0.0853 0.4629 1.0000
2.250 0.7231 0.01597 0.00566 -0.0841 0.4487 1.0000
2.500 0.7451 0.01629 0.00584 -0.0831 0.4367 1.0000
3.000 0.7896 0.01694 0.00627 -0.0810 0.4157 1.0000
3.250 0.8120 0.01727 0.00650 -0.0801 0.4069 1.0000
3.500 0.8344 0.01760 0.00676 -0.0792 0.3984 1.0000
3.750 0.8572 0.01794 0.00707 -0.0783 0.3910 1.0000
4.000 0.8801 0.01828 0.00737 -0.0775 0.3842 1.0000
4.250 0.9032 0.01865 0.00770 -0.0768 0.3783 1.0000
4.500 0.9261 0.01900 0.00808 -0.0760 0.3719 1.0000
4.750 0.9491 0.01939 0.00843 -0.0753 0.3664 1.0000
5.000 0.9719 0.01976 0.00885 -0.0745 0.3606 1.0000
5.250 0.9946 0.02015 0.00926 -0.0737 0.3549 1.0000
5.500 1.0184 0.02058 0.00970 -0.0732 0.3508 1.0000
5.750 1.0410 0.02099 0.01022 -0.0724 0.3458 1.0000
6.000 1.0641 0.02142 0.01073 -0.0717 0.3413 1.0000
6.250 1.0876 0.02188 0.01123 -0.0712 0.3374 1.0000
6.500 1.1105 0.02236 0.01183 -0.0705 0.3332 1.0000
6.750 1.1323 0.02282 0.01245 -0.0696 0.3285 1.0000
7.000 1.1550 0.02331 0.01305 -0.0689 0.3246 1.0000
7.500 1.1914 0.02408 0.01409 -0.0658 0.3104 1.0000
7.750 1.2024 0.02428 0.01438 -0.0628 0.2981 1.0000
8.000 1.2172 0.02459 0.01476 -0.0605 0.2895 1.0000
8.250 1.2284 0.02486 0.01519 -0.0577 0.2781 1.0000
8.500 1.2367 0.02513 0.01559 -0.0543 0.2635 1.0000
8.750 1.2432 0.02546 0.01603 -0.0506 0.2466 1.0000
9.000 1.2451 0.02587 0.01647 -0.0462 0.2180 1.0000
9.250 1.2418 0.02688 0.01716 -0.0415 0.1512 1.0000
9.500 1.2191 0.02986 0.01932 -0.0351 0.0581 1.0000
9.750 1.2095 0.03222 0.02157 -0.0305 0.0381 1.0000
10.000 1.2092 0.03392 0.02341 -0.0273 0.0331 1.0000
10.250 1.2048 0.03597 0.02559 -0.0240 0.0294 1.0000
10.500 1.2046 0.03776 0.02758 -0.0214 0.0279 1.0000
10.750 1.1996 0.04003 0.03004 -0.0189 0.0254 1.0000
11.000 1.1944 0.04245 0.03265 -0.0167 0.0247 1.0000
11.250 1.1849 0.04543 0.03583 -0.0149 0.0240 1.0000
11.500 1.1732 0.04892 0.03952 -0.0136 0.0235 1.0000
11.750 1.1577 0.05322 0.04400 -0.0131 0.0231 1.0000
12.000 1.1433 0.05788 0.04887 -0.0135 0.0229 1.0000
12.250 1.1251 0.06357 0.05475 -0.0147 0.0227 1.0000
12.500 1.1100 0.06925 0.06061 -0.0163 0.0227 1.0000
12.750 1.0952 0.07509 0.06657 -0.0181 0.0226 1.0000
13.000 1.0824 0.08062 0.07227 -0.0197 0.0225 1.0000
13.250 1.0723 0.08566 0.07743 -0.0210 0.0223 1.0000
13.500 1.0641 0.09031 0.08224 -0.0220 0.0221 1.0000
13.750 1.0585 0.09445 0.08649 -0.0228 0.0215 1.0000
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Polar data table (+)
Polar graphs
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