Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 50,000 Max Cl/Cd: 30.49 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg4-il-50000.txt Download as CSV file: xf-fg4-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2593 0.15511 0.14819 -0.0324 1.0000 0.1337
-12.750 -0.3199 0.15406 0.14640 -0.0297 1.0000 0.1327
-12.500 -0.3359 0.15525 0.14771 -0.0314 1.0000 0.1336
-12.250 -0.3062 0.14638 0.13883 -0.0292 1.0000 0.1370
-12.000 -0.2960 0.14282 0.13530 -0.0284 1.0000 0.1414
-11.750 -0.2939 0.14052 0.13306 -0.0283 1.0000 0.1458
-11.500 -0.3008 0.13961 0.13223 -0.0289 1.0000 0.1497
-11.250 -0.3191 0.14044 0.13319 -0.0301 1.0000 0.1514
-5.500 -0.4654 0.09217 0.08698 0.0073 1.0000 0.2839
-5.250 -0.4558 0.08883 0.08377 0.0119 1.0000 0.2932
-5.000 -0.4723 0.08730 0.08230 0.0131 1.0000 0.3065
-4.750 -0.4836 0.08602 0.08104 0.0147 1.0000 0.3239
-4.500 0.0838 0.06412 0.05850 -0.0204 1.0000 1.0000
-4.250 0.0790 0.06366 0.05817 -0.0185 1.0000 1.0000
-4.000 0.0722 0.06342 0.05807 -0.0165 1.0000 1.0000
-3.750 0.0643 0.06338 0.05815 -0.0146 1.0000 1.0000
-3.500 0.0558 0.06340 0.05830 -0.0127 1.0000 1.0000
-3.250 0.0479 0.06345 0.05846 -0.0110 1.0000 1.0000
-3.000 0.0252 0.06312 0.05829 -0.0065 0.9885 0.9793
-2.750 -0.0271 0.06296 0.05825 0.0030 0.9667 0.9234
-2.500 -0.0831 0.06257 0.05797 0.0117 0.9495 0.8746
-2.250 -0.1374 0.06150 0.05701 0.0187 0.9340 0.8279
-2.000 -0.1956 0.06031 0.05593 0.0273 0.9207 0.8038
-1.750 -0.2532 0.05884 0.05456 0.0367 0.9083 0.7877
-1.500 -0.3081 0.05699 0.05277 0.0442 0.8974 0.7669
-1.250 -0.1688 0.05414 0.04657 -0.0159 0.8767 0.2839
-1.000 -0.1208 0.05241 0.04409 -0.0188 0.8654 0.2241
-0.750 -0.0839 0.05101 0.04220 -0.0197 0.8532 0.1971
-0.500 -0.0592 0.05040 0.04119 -0.0189 0.8406 0.1821
-0.250 -0.0248 0.05017 0.04033 -0.0190 0.8285 0.1695
0.000 0.0250 0.04887 0.03883 -0.0221 0.8171 0.1654
0.250 0.0492 0.04843 0.03821 -0.0217 0.8033 0.1630
0.500 0.0812 0.04806 0.03759 -0.0222 0.7899 0.1586
0.750 0.1248 0.04775 0.03698 -0.0246 0.7769 0.1550
1.000 0.2083 0.04698 0.03598 -0.0338 0.7630 0.1548
1.250 0.2841 0.04599 0.03497 -0.0412 0.7499 0.1638
1.500 0.3159 0.04615 0.03505 -0.0421 0.7347 0.1699
1.750 0.5151 0.04186 0.03320 -0.0718 0.7193 1.0000
2.000 0.5442 0.04220 0.03312 -0.0709 0.7047 1.0000
2.250 0.6194 0.04020 0.03066 -0.0753 0.6967 1.0000
2.500 0.6379 0.04084 0.03116 -0.0735 0.6805 1.0000
2.750 0.6570 0.04152 0.03172 -0.0719 0.6650 1.0000
3.000 0.6842 0.04185 0.03195 -0.0712 0.6507 1.0000
3.250 0.7840 0.03863 0.02855 -0.0792 0.6390 1.0000
3.500 0.8454 0.03686 0.02665 -0.0824 0.6206 1.0000
3.750 0.8882 0.03589 0.02556 -0.0831 0.6012 1.0000
4.000 0.9267 0.03524 0.02480 -0.0835 0.5824 1.0000
4.250 0.9611 0.03487 0.02431 -0.0834 0.5645 1.0000
4.500 0.9950 0.03467 0.02402 -0.0835 0.5481 1.0000
4.750 1.0335 0.03443 0.02363 -0.0845 0.5329 1.0000
5.000 1.0349 0.03552 0.02478 -0.0800 0.5186 1.0000
5.250 1.0442 0.03651 0.02579 -0.0769 0.5059 1.0000
5.500 1.0710 0.03663 0.02585 -0.0762 0.4922 1.0000
5.750 1.1080 0.03634 0.02543 -0.0769 0.4785 1.0000
6.000 1.1076 0.03738 0.02657 -0.0722 0.4655 1.0000
6.250 1.1179 0.03811 0.02733 -0.0692 0.4534 1.0000
6.500 1.1441 0.03798 0.02712 -0.0683 0.4402 1.0000
6.750 1.1597 0.03856 0.02772 -0.0662 0.4294 1.0000
7.000 1.1644 0.03969 0.02893 -0.0627 0.4198 1.0000
7.250 1.2008 0.03952 0.02870 -0.0636 0.4098 1.0000
7.500 1.1878 0.04137 0.03074 -0.0576 0.4010 1.0000
7.750 1.2214 0.04111 0.03040 -0.0580 0.3904 1.0000
8.000 1.2141 0.04256 0.03199 -0.0529 0.3810 1.0000
8.250 1.2297 0.04286 0.03231 -0.0507 0.3702 1.0000
8.500 1.2666 0.04228 0.03160 -0.0515 0.3578 1.0000
8.750 1.2403 0.04426 0.03381 -0.0437 0.3496 1.0000
9.000 1.2566 0.04417 0.03366 -0.0415 0.3367 1.0000
9.250 1.2752 0.04397 0.03336 -0.0396 0.3225 1.0000
9.500 1.2647 0.04531 0.03487 -0.0344 0.3113 1.0000
9.750 1.2625 0.04649 0.03612 -0.0306 0.2994 1.0000
10.000 1.2624 0.04725 0.03685 -0.0269 0.2838 1.0000
10.250 1.2617 0.04833 0.03790 -0.0235 0.2683 1.0000
10.500 1.2557 0.04983 0.03935 -0.0198 0.2518 1.0000
10.750 1.2484 0.05170 0.04116 -0.0165 0.2352 1.0000
11.000 1.2476 0.05355 0.04291 -0.0140 0.2208 1.0000
11.250 1.2563 0.05498 0.04418 -0.0123 0.2080 1.0000
11.500 1.2370 0.05880 0.04822 -0.0097 0.2001 1.0000
11.750 1.2532 0.06005 0.04934 -0.0087 0.1918 1.0000
12.000 1.2324 0.06456 0.05414 -0.0069 0.1877 1.0000
12.250 1.2238 0.06830 0.05802 -0.0058 0.1838 1.0000
12.500 1.2647 0.06783 0.05731 -0.0054 0.1784 1.0000
12.750 1.2249 0.07449 0.06434 -0.0044 0.1772 1.0000
13.000 1.1639 0.08472 0.07492 -0.0054 0.1769 1.0000
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Polar data table (+)
Polar graphs
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