Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 100,000 Max Cl/Cd: 47.32 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg4-il-100000-n5.txt Download as CSV file: xf-fg4-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 4
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 -0.2725 0.09593 0.09116 -0.0420 0.9806 0.0656
-8.000 -0.2856 0.09229 0.08748 -0.0511 0.9673 0.0665
-7.750 -0.2782 0.08779 0.08295 -0.0547 0.9583 0.0669
-7.500 -0.2573 0.08424 0.07947 -0.0535 0.9551 0.0677
-7.250 -0.2434 0.08118 0.07644 -0.0534 0.9479 0.0689
-7.000 -0.2256 0.07759 0.07282 -0.0562 0.9416 0.0704
-6.750 -0.2137 0.07412 0.06932 -0.0584 0.9319 0.0723
-6.500 -0.2040 0.07024 0.06507 -0.0652 0.9191 0.0770
-6.250 -0.1907 0.06595 0.06067 -0.0668 0.9114 0.0780
-6.000 -0.1705 0.06244 0.05726 -0.0670 0.9055 0.0792
-5.750 -0.1453 0.05930 0.05411 -0.0686 0.9015 0.0813
-5.500 -0.1315 0.05679 0.05154 -0.0682 0.8911 0.0838
-5.000 -0.0961 0.05097 0.04536 -0.0694 0.8736 0.0935
-4.750 -0.0682 0.04840 0.04273 -0.0707 0.8687 0.0980
-4.250 -0.0406 0.04412 0.03816 -0.0678 0.8453 0.1102
-3.750 -0.0049 0.03757 0.03058 -0.0627 0.8219 0.0682
-3.500 0.0168 0.03487 0.02753 -0.0608 0.8119 0.0559
-3.250 0.0380 0.03296 0.02542 -0.0593 0.8013 0.0539
-3.000 0.0553 0.03116 0.02290 -0.0557 0.7884 0.0500
-2.750 0.0832 0.02950 0.02110 -0.0555 0.7791 0.0496
-2.500 0.1102 0.02806 0.01933 -0.0548 0.7683 0.0503
-2.250 0.1384 0.02671 0.01787 -0.0546 0.7566 0.0510
-2.000 0.1770 0.02529 0.01615 -0.0561 0.7468 0.0511
-1.750 0.2107 0.02426 0.01472 -0.0563 0.7333 0.0503
-1.500 0.2465 0.02329 0.01350 -0.0574 0.7199 0.0500
-1.000 0.3276 0.02143 0.01129 -0.0617 0.6946 0.0503
-0.750 0.3602 0.02080 0.01059 -0.0624 0.6813 0.0507
-0.500 0.3972 0.02022 0.00996 -0.0641 0.6688 0.0515
-0.250 0.4301 0.01982 0.00953 -0.0650 0.6561 0.0539
0.000 0.4556 0.01952 0.00919 -0.0643 0.6424 0.0557
0.250 0.4808 0.01924 0.00884 -0.0634 0.6266 0.0567
0.500 0.5040 0.01903 0.00852 -0.0621 0.6099 0.0575
0.750 0.5265 0.01882 0.00822 -0.0608 0.5933 0.0587
1.000 0.5486 0.01870 0.00799 -0.0594 0.5766 0.0604
1.250 0.5724 0.01866 0.00783 -0.0584 0.5608 0.0630
1.500 0.5966 0.01868 0.00775 -0.0575 0.5454 0.0673
1.750 0.6219 0.01869 0.00768 -0.0569 0.5296 0.0740
2.000 0.6451 0.01873 0.00764 -0.0559 0.5120 0.0830
2.500 0.8559 0.01817 0.00870 -0.0903 0.4451 1.0000
2.750 0.8718 0.01844 0.00884 -0.0879 0.4281 1.0000
3.000 0.8868 0.01874 0.00901 -0.0853 0.4091 1.0000
3.250 0.8995 0.01907 0.00918 -0.0823 0.3865 1.0000
3.500 0.9104 0.01945 0.00936 -0.0790 0.3639 1.0000
3.750 0.9232 0.01983 0.00959 -0.0761 0.3464 1.0000
4.000 0.9363 0.02023 0.00987 -0.0733 0.3299 1.0000
4.250 0.9503 0.02062 0.01016 -0.0708 0.3163 1.0000
4.500 0.9639 0.02105 0.01049 -0.0682 0.3033 1.0000
4.750 0.9781 0.02147 0.01084 -0.0658 0.2902 1.0000
5.000 0.9932 0.02189 0.01122 -0.0635 0.2793 1.0000
5.250 1.0069 0.02236 0.01162 -0.0611 0.2676 1.0000
5.500 1.0206 0.02284 0.01204 -0.0587 0.2545 1.0000
5.750 1.0340 0.02336 0.01250 -0.0564 0.2406 1.0000
6.000 1.0473 0.02389 0.01299 -0.0540 0.2284 1.0000
6.250 1.0600 0.02446 0.01351 -0.0516 0.2166 1.0000
6.500 1.0726 0.02506 0.01406 -0.0493 0.2035 1.0000
6.750 1.0848 0.02570 0.01466 -0.0470 0.1900 1.0000
7.000 1.0964 0.02639 0.01531 -0.0447 0.1766 1.0000
7.250 1.1041 0.02731 0.01610 -0.0419 0.1548 1.0000
7.500 1.1123 0.02824 0.01694 -0.0393 0.1358 1.0000
7.750 1.1191 0.02929 0.01789 -0.0367 0.1172 1.0000
8.000 1.1161 0.03105 0.01935 -0.0331 0.0836 1.0000
8.250 1.1216 0.03230 0.02056 -0.0307 0.0787 1.0000
8.500 1.1291 0.03345 0.02173 -0.0285 0.0764 1.0000
8.750 1.1361 0.03467 0.02298 -0.0265 0.0751 1.0000
9.000 1.1429 0.03593 0.02429 -0.0245 0.0740 1.0000
9.250 1.1492 0.03727 0.02570 -0.0227 0.0733 1.0000
9.500 1.1549 0.03870 0.02720 -0.0209 0.0726 1.0000
9.750 1.1596 0.04025 0.02886 -0.0193 0.0721 1.0000
10.000 1.1639 0.04191 0.03060 -0.0177 0.0718 1.0000
10.250 1.1659 0.04383 0.03262 -0.0163 0.0712 1.0000
10.500 1.1687 0.04576 0.03466 -0.0151 0.0711 1.0000
10.750 1.1687 0.04805 0.03705 -0.0139 0.0707 1.0000
11.000 1.1694 0.05038 0.03950 -0.0131 0.0705 1.0000
11.250 1.1690 0.05290 0.04214 -0.0124 0.0704 1.0000
11.500 1.1649 0.05594 0.04529 -0.0119 0.0700 1.0000
11.750 1.1651 0.05861 0.04809 -0.0115 0.0701 1.0000
12.000 1.1618 0.06177 0.05135 -0.0114 0.0698 1.0000
12.250 1.1577 0.06511 0.05481 -0.0114 0.0697 1.0000
12.500 1.1554 0.06832 0.05813 -0.0115 0.0697 1.0000
12.750 1.1532 0.07157 0.06150 -0.0117 0.0697 1.0000
13.000 1.1512 0.07483 0.06488 -0.0119 0.0696 1.0000
13.250 1.1493 0.07810 0.06825 -0.0122 0.0695 1.0000
13.500 1.1484 0.08127 0.07150 -0.0125 0.0694 1.0000
13.750 1.1494 0.08416 0.07448 -0.0127 0.0694 1.0000
14.000 1.1512 0.08693 0.07734 -0.0130 0.0694 1.0000
14.250 1.1545 0.08948 0.07996 -0.0131 0.0693 1.0000
14.500 1.1594 0.09175 0.08231 -0.0132 0.0693 1.0000
14.750 1.1651 0.09393 0.08455 -0.0132 0.0692 1.0000
15.000 1.1718 0.09595 0.08663 -0.0132 0.0692 1.0000
15.250 1.1782 0.09800 0.08875 -0.0133 0.0689 1.0000
15.500 1.1827 0.10045 0.09130 -0.0136 0.0686 1.0000
15.750 1.1877 0.10280 0.09376 -0.0139 0.0682 1.0000
16.000 1.1900 0.10565 0.09672 -0.0145 0.0676 1.0000
16.250 1.1924 0.10847 0.09964 -0.0151 0.0668 1.0000
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Polar data table (+)
Polar graphs
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