Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 100,000 Max Cl/Cd: 52.67 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg1-il-100000-n5.txt Download as CSV file: xf-fg1-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 1
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4162 0.09249 0.08747 -0.0278 1.0000 0.0594
-8.250 -0.4324 0.09057 0.08565 -0.0283 1.0000 0.0603
-8.000 -0.4473 0.08816 0.08329 -0.0318 1.0000 0.0611
-7.750 -0.4564 0.08569 0.08075 -0.0333 1.0000 0.0614
-7.500 -0.4539 0.08136 0.07653 -0.0305 1.0000 0.0621
-7.250 -0.4506 0.07853 0.07376 -0.0271 1.0000 0.0631
-7.000 -0.4492 0.07605 0.07131 -0.0250 1.0000 0.0644
-6.750 -0.4481 0.07349 0.06875 -0.0239 1.0000 0.0660
-6.500 -0.4459 0.07078 0.06601 -0.0234 1.0000 0.0680
-6.250 -0.4404 0.06902 0.06370 -0.0280 1.0000 0.0737
-5.750 -0.4152 0.06073 0.05567 -0.0271 0.9963 0.0777
-5.250 -0.3652 0.05372 0.04813 -0.0336 0.9876 0.0900
-5.000 -0.3438 0.05079 0.04521 -0.0343 0.9844 0.0927
-4.750 -0.3202 0.04830 0.04255 -0.0355 0.9798 0.0991
-4.500 -0.2943 0.04520 0.03919 -0.0375 0.9759 0.1071
-4.250 -0.2703 0.04358 0.03732 -0.0380 0.9708 0.1171
-4.000 -0.2481 0.04077 0.03452 -0.0387 0.9668 0.1265
-3.750 -0.2069 0.03515 0.02760 -0.0384 0.9627 0.0628
-3.500 -0.1792 0.03292 0.02522 -0.0387 0.9569 0.0575
-3.250 -0.1434 0.03050 0.02201 -0.0392 0.9517 0.0515
-3.000 -0.1132 0.02898 0.02023 -0.0395 0.9441 0.0502
-2.750 -0.0774 0.02766 0.01857 -0.0408 0.9393 0.0506
-2.500 -0.0512 0.02645 0.01712 -0.0404 0.9323 0.0511
-2.250 -0.0169 0.02519 0.01567 -0.0415 0.9280 0.0506
-2.000 0.0132 0.02402 0.01436 -0.0418 0.9223 0.0501
-1.750 0.0453 0.02300 0.01322 -0.0424 0.9165 0.0497
-1.500 0.0835 0.02199 0.01210 -0.0442 0.9126 0.0494
-1.250 0.1123 0.02125 0.01130 -0.0440 0.9049 0.0494
-1.000 0.1496 0.02041 0.01043 -0.0456 0.8997 0.0495
-0.750 0.1838 0.01970 0.00972 -0.0465 0.8936 0.0498
-0.500 0.2160 0.01902 0.00909 -0.0471 0.8860 0.0517
-0.250 0.2562 0.01824 0.00840 -0.0493 0.8814 0.0537
0.000 0.2822 0.01785 0.00803 -0.0486 0.8706 0.0543
0.250 0.3161 0.01743 0.00759 -0.0494 0.8623 0.0553
0.500 0.3525 0.01702 0.00715 -0.0507 0.8531 0.0567
0.750 0.3832 0.01673 0.00683 -0.0508 0.8400 0.0585
1.000 0.4151 0.01644 0.00650 -0.0512 0.8254 0.0611
1.250 0.4481 0.01607 0.00616 -0.0516 0.8074 0.0685
1.750 0.6038 0.01343 0.00571 -0.0723 0.7461 1.0000
2.000 0.6368 0.01337 0.00547 -0.0728 0.7102 1.0000
2.250 0.6695 0.01340 0.00529 -0.0733 0.6684 1.0000
2.500 0.6982 0.01357 0.00522 -0.0730 0.6230 1.0000
2.750 0.7230 0.01386 0.00525 -0.0721 0.5803 1.0000
3.000 0.7457 0.01422 0.00538 -0.0708 0.5448 1.0000
3.250 0.7674 0.01459 0.00559 -0.0695 0.5140 1.0000
3.500 0.7885 0.01497 0.00584 -0.0680 0.4856 1.0000
3.750 0.8090 0.01537 0.00611 -0.0665 0.4575 1.0000
4.000 0.8289 0.01579 0.00642 -0.0649 0.4294 1.0000
4.250 0.8485 0.01621 0.00674 -0.0632 0.4015 1.0000
4.500 0.8680 0.01663 0.00709 -0.0616 0.3748 1.0000
4.750 0.8870 0.01710 0.00746 -0.0599 0.3494 1.0000
5.000 0.9056 0.01760 0.00787 -0.0582 0.3241 1.0000
5.250 0.9240 0.01812 0.00830 -0.0564 0.2993 1.0000
5.500 0.9419 0.01867 0.00875 -0.0547 0.2766 1.0000
5.750 0.9602 0.01922 0.00923 -0.0530 0.2570 1.0000
6.000 0.9788 0.01977 0.00976 -0.0514 0.2406 1.0000
6.250 0.9973 0.02033 0.01030 -0.0498 0.2267 1.0000
6.500 1.0153 0.02093 0.01086 -0.0482 0.2150 1.0000
6.750 1.0340 0.02149 0.01148 -0.0466 0.2035 1.0000
7.000 1.0524 0.02210 0.01215 -0.0451 0.1928 1.0000
7.250 1.0695 0.02276 0.01282 -0.0434 0.1829 1.0000
7.500 1.0868 0.02341 0.01354 -0.0417 0.1726 1.0000
7.750 1.1040 0.02408 0.01430 -0.0400 0.1620 1.0000
8.000 1.1196 0.02481 0.01509 -0.0381 0.1517 1.0000
8.250 1.1346 0.02550 0.01586 -0.0362 0.1404 1.0000
8.500 1.1493 0.02610 0.01657 -0.0342 0.1264 1.0000
8.750 1.1630 0.02672 0.01722 -0.0321 0.1115 1.0000
9.000 1.1757 0.02742 0.01798 -0.0299 0.0969 1.0000
9.250 1.1854 0.02831 0.01886 -0.0273 0.0863 1.0000
9.500 1.1947 0.02933 0.01992 -0.0247 0.0759 1.0000
9.750 1.2026 0.03048 0.02115 -0.0219 0.0675 1.0000
10.000 1.2072 0.03183 0.02251 -0.0190 0.0606 1.0000
10.250 1.2136 0.03316 0.02398 -0.0163 0.0534 1.0000
10.500 1.2163 0.03473 0.02563 -0.0134 0.0480 1.0000
10.750 1.2196 0.03630 0.02734 -0.0108 0.0436 1.0000
11.000 1.2190 0.03814 0.02923 -0.0081 0.0412 1.0000
11.250 1.2207 0.04001 0.03128 -0.0057 0.0383 1.0000
11.500 1.2214 0.04195 0.03338 -0.0036 0.0362 1.0000
11.750 1.2198 0.04408 0.03561 -0.0017 0.0342 1.0000
12.000 1.2157 0.04655 0.03813 0.0000 0.0329 1.0000
12.250 1.2141 0.04908 0.04093 0.0014 0.0312 1.0000
12.500 1.2108 0.05185 0.04390 0.0026 0.0303 1.0000
12.750 1.2063 0.05488 0.04710 0.0033 0.0294 1.0000
13.000 1.2010 0.05814 0.05053 0.0037 0.0287 1.0000
13.250 1.1943 0.06173 0.05427 0.0036 0.0281 1.0000
13.500 1.1874 0.06554 0.05823 0.0032 0.0276 1.0000
13.750 1.1795 0.06965 0.06248 0.0023 0.0272 1.0000
14.000 1.1709 0.07404 0.06698 0.0011 0.0267 1.0000
14.250 1.1611 0.07884 0.07189 -0.0004 0.0263 1.0000
14.500 1.1482 0.08451 0.07779 -0.0028 0.0260 1.0000
14.750 1.1340 0.09069 0.08418 -0.0056 0.0258 1.0000
15.000 1.1189 0.09722 0.09091 -0.0087 0.0258 1.0000
15.250 1.0998 0.10499 0.09888 -0.0129 0.0256 1.0000
15.500 1.0818 0.11277 0.10683 -0.0170 0.0257 1.0000
15.750 1.0598 0.12187 0.11610 -0.0219 0.0258 1.0000
16.000 1.0337 0.13258 0.12696 -0.0280 0.0259 1.0000
16.250 1.0095 0.14337 0.13786 -0.0338 0.0262 1.0000
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Polar data table (+)
Polar graphs
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