Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 50,000 Max Cl/Cd: 33.16 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg2-il-50000.txt Download as CSV file: xf-fg2-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4217 0.10571 0.09898 -0.0158 1.0000 0.1762
-8.250 -0.4114 0.10156 0.09484 -0.0144 1.0000 0.1866
-8.000 -0.4299 0.10068 0.09413 -0.0153 1.0000 0.1917
-7.750 -0.4203 0.09669 0.09017 -0.0136 1.0000 0.2047
-7.500 -0.4175 0.09337 0.08693 -0.0124 1.0000 0.2140
-7.250 -0.4383 0.09241 0.08613 -0.0139 1.0000 0.2218
-7.000 -0.4323 0.08890 0.08269 -0.0121 1.0000 0.2359
-6.750 -0.4309 0.08586 0.07972 -0.0108 1.0000 0.2506
-6.500 -0.4350 0.08337 0.07732 -0.0103 1.0000 0.2663
-6.250 -0.4217 0.07930 0.07330 -0.0060 1.0000 0.2886
-6.000 -0.4294 0.07739 0.07149 -0.0053 1.0000 0.3105
-5.750 -0.4263 0.07449 0.06868 -0.0016 1.0000 0.3399
-5.500 -0.4163 0.07132 0.06559 0.0043 1.0000 0.3801
-5.250 -0.0174 0.04781 0.04072 -0.0223 1.0000 1.0000
-5.000 -0.0077 0.04574 0.03871 -0.0229 1.0000 1.0000
-4.750 0.0021 0.04373 0.03674 -0.0233 1.0000 1.0000
-4.500 -0.0317 0.04449 0.03771 -0.0130 1.0000 0.9760
-4.250 -0.0914 0.04603 0.03958 0.0017 1.0000 0.9246
-4.000 -0.1466 0.04692 0.04075 0.0133 1.0000 0.8766
-3.750 -0.1973 0.04685 0.04095 0.0220 1.0000 0.8240
-3.500 -0.2454 0.04644 0.04083 0.0302 1.0000 0.7903
-3.250 -0.2934 0.04568 0.04036 0.0384 1.0000 0.7642
-3.000 -0.3381 0.04473 0.03966 0.0465 1.0000 0.7498
-2.750 -0.2793 0.03827 0.03105 -0.0099 1.0000 0.3110
-2.500 -0.2371 0.03545 0.02713 -0.0127 1.0000 0.2208
-2.250 -0.2111 0.03347 0.02457 -0.0119 1.0000 0.1900
-2.000 -0.1882 0.03186 0.02253 -0.0107 1.0000 0.1731
-1.750 -0.1663 0.03088 0.02099 -0.0091 1.0000 0.1619
-1.500 -0.1477 0.02976 0.01968 -0.0078 1.0000 0.1601
-1.250 -0.1293 0.02888 0.01860 -0.0065 1.0000 0.1579
-1.000 -0.1102 0.02821 0.01765 -0.0055 1.0000 0.1535
-0.750 -0.0920 0.02789 0.01702 -0.0044 1.0000 0.1500
-0.500 -0.0749 0.02776 0.01669 -0.0034 1.0000 0.1483
-0.250 -0.0313 0.02752 0.01623 -0.0072 0.9929 0.1481
0.000 0.0431 0.02704 0.01569 -0.0164 0.9745 0.1580
0.250 0.1055 0.02667 0.01528 -0.0233 0.9536 0.1697
0.500 0.1715 0.02612 0.01488 -0.0308 0.9344 0.2015
0.750 0.2861 0.02379 0.01425 -0.0471 0.9182 1.0000
1.000 0.3464 0.02383 0.01392 -0.0531 0.8949 1.0000
1.250 0.4058 0.02367 0.01354 -0.0587 0.8719 1.0000
1.500 0.4707 0.02326 0.01301 -0.0650 0.8503 1.0000
1.750 0.5205 0.02305 0.01272 -0.0684 0.8258 1.0000
2.000 0.5752 0.02268 0.01228 -0.0724 0.8034 1.0000
2.250 0.6129 0.02275 0.01232 -0.0736 0.7788 1.0000
2.500 0.6490 0.02291 0.01242 -0.0744 0.7559 1.0000
2.750 0.6832 0.02318 0.01266 -0.0750 0.7348 1.0000
3.000 0.7141 0.02362 0.01305 -0.0751 0.7153 1.0000
3.250 0.7380 0.02432 0.01379 -0.0743 0.6963 1.0000
3.500 0.7629 0.02503 0.01452 -0.0736 0.6794 1.0000
3.750 0.7871 0.02580 0.01531 -0.0728 0.6634 1.0000
4.000 0.8110 0.02652 0.01605 -0.0718 0.6471 1.0000
4.250 0.8370 0.02698 0.01653 -0.0706 0.6285 1.0000
4.500 0.8546 0.02770 0.01730 -0.0684 0.6081 1.0000
4.750 0.8774 0.02821 0.01783 -0.0667 0.5888 1.0000
5.000 0.9007 0.02881 0.01848 -0.0653 0.5717 1.0000
5.250 0.9225 0.02952 0.01929 -0.0638 0.5549 1.0000
5.500 0.9393 0.03045 0.02037 -0.0617 0.5375 1.0000
5.750 0.9574 0.03130 0.02135 -0.0597 0.5193 1.0000
6.000 0.9785 0.03200 0.02215 -0.0580 0.5006 1.0000
6.250 1.0028 0.03260 0.02281 -0.0565 0.4817 1.0000
6.500 1.0152 0.03384 0.02432 -0.0538 0.4614 1.0000
6.750 1.0371 0.03455 0.02511 -0.0520 0.4406 1.0000
7.000 1.0541 0.03563 0.02634 -0.0498 0.4205 1.0000
7.250 1.0689 0.03700 0.02790 -0.0475 0.4020 1.0000
7.500 1.0847 0.03856 0.02966 -0.0455 0.3863 1.0000
7.750 1.1058 0.03935 0.03062 -0.0437 0.3689 1.0000
8.000 1.1244 0.03952 0.03088 -0.0414 0.3474 1.0000
8.250 1.1465 0.03796 0.02924 -0.0388 0.3170 1.0000
8.500 1.1599 0.03629 0.02750 -0.0351 0.2842 1.0000
8.750 1.1651 0.03514 0.02632 -0.0306 0.2520 1.0000
9.000 1.1589 0.03505 0.02633 -0.0248 0.2142 1.0000
9.250 1.1450 0.03639 0.02711 -0.0185 0.1690 1.0000
9.500 1.1357 0.03939 0.02976 -0.0137 0.1336 1.0000
9.750 1.1405 0.04224 0.03231 -0.0107 0.1137 1.0000
10.000 1.1521 0.04500 0.03521 -0.0085 0.1019 1.0000
10.250 1.1637 0.04799 0.03843 -0.0065 0.0942 1.0000
10.500 1.1787 0.05058 0.04089 -0.0053 0.0870 1.0000
10.750 1.1759 0.05355 0.04435 -0.0020 0.0839 1.0000
11.000 1.1745 0.05669 0.04782 0.0007 0.0814 1.0000
11.250 1.1717 0.06003 0.05143 0.0031 0.0795 1.0000
11.500 1.1641 0.06363 0.05530 0.0053 0.0788 1.0000
11.750 1.1507 0.06757 0.05951 0.0071 0.0785 1.0000
12.000 1.1284 0.07216 0.06438 0.0081 0.0788 1.0000
12.250 1.0965 0.07797 0.07049 0.0071 0.0801 1.0000
12.500 1.0620 0.08517 0.07790 0.0039 0.0816 1.0000
12.750 1.0296 0.09351 0.08637 -0.0006 0.0837 1.0000
13.000 1.0022 0.10229 0.09521 -0.0054 0.0855 1.0000
13.250 0.9821 0.11068 0.10361 -0.0094 0.0868 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Fage & Collins 2 (fg2-il)