GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 457 AIRFOIL (goe457-il) Reynolds number: 50,000 Max Cl/Cd: 34.47 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe457-il-50000.txt Download as CSV file: xf-goe457-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 457 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3875 0.10634 0.09980 -0.0199 1.0000 0.1719
-7.500 -0.3565 0.09924 0.09261 -0.0176 1.0000 0.1816
-7.250 -0.3754 0.09916 0.09271 -0.0174 1.0000 0.1859
-7.000 -0.3653 0.09483 0.08843 -0.0155 1.0000 0.1918
-6.750 -0.3707 0.09320 0.08690 -0.0155 1.0000 0.1999
-6.500 -0.3681 0.08995 0.08374 -0.0143 1.0000 0.2064
-6.250 -0.3756 0.08884 0.08273 -0.0159 1.0000 0.2163
-6.000 -0.3669 0.08498 0.07892 -0.0126 1.0000 0.2276
-5.750 -0.3661 0.08225 0.07627 -0.0119 1.0000 0.2377
-5.500 -0.3666 0.07987 0.07397 -0.0122 1.0000 0.2501
-5.250 -0.3646 0.07742 0.07157 -0.0122 1.0000 0.2640
-5.000 -0.3603 0.07460 0.06880 -0.0111 1.0000 0.2792
-4.750 -0.3550 0.07164 0.06590 -0.0090 1.0000 0.2957
-4.500 -0.3495 0.06890 0.06320 -0.0069 1.0000 0.3149
-4.250 -0.3456 0.06629 0.06065 -0.0058 1.0000 0.3400
-4.000 -0.3418 0.06373 0.05816 -0.0026 1.0000 0.3703
-3.750 -0.3392 0.06125 0.05577 0.0023 1.0000 0.4068
-3.500 -0.3390 0.05881 0.05344 0.0078 1.0000 0.4492
-2.750 -0.3488 0.05193 0.04688 0.0307 1.0000 0.6063
-2.500 -0.3507 0.04955 0.04461 0.0378 1.0000 0.6527
-2.250 -0.0980 0.03655 0.02830 -0.0459 1.0000 0.1874
-2.000 -0.0666 0.03376 0.02495 -0.0470 1.0000 0.1713
-1.750 -0.0407 0.03173 0.02270 -0.0471 1.0000 0.1668
-1.500 -0.0147 0.03023 0.02084 -0.0472 1.0000 0.1674
-1.250 0.0100 0.02899 0.01924 -0.0470 1.0000 0.1681
-1.000 0.0341 0.02794 0.01791 -0.0467 1.0000 0.1680
-0.750 0.0555 0.02724 0.01694 -0.0461 1.0000 0.1698
-0.500 0.0743 0.02682 0.01634 -0.0454 1.0000 0.1730
-0.250 0.0913 0.02675 0.01625 -0.0449 1.0000 0.1817
0.000 0.1206 0.02693 0.01635 -0.0468 0.9955 0.1972
0.250 0.1906 0.02649 0.01599 -0.0547 0.9748 0.2489
0.500 0.2595 0.02387 0.01503 -0.0616 0.9558 1.0000
0.750 0.3247 0.02454 0.01523 -0.0690 0.9299 1.0000
1.000 0.3795 0.02489 0.01531 -0.0742 0.9031 1.0000
1.250 0.4304 0.02508 0.01532 -0.0783 0.8780 1.0000
1.500 0.4883 0.02491 0.01502 -0.0830 0.8568 1.0000
1.750 0.5323 0.02484 0.01485 -0.0853 0.8331 1.0000
2.000 0.5833 0.02443 0.01438 -0.0883 0.8134 1.0000
2.250 0.6217 0.02431 0.01421 -0.0892 0.7915 1.0000
2.500 0.6645 0.02399 0.01385 -0.0905 0.7718 1.0000
2.750 0.7061 0.02371 0.01351 -0.0916 0.7529 1.0000
3.000 0.7365 0.02394 0.01373 -0.0913 0.7316 1.0000
3.250 0.7712 0.02406 0.01380 -0.0914 0.7126 1.0000
3.500 0.8052 0.02428 0.01395 -0.0915 0.6944 1.0000
3.750 0.8289 0.02503 0.01475 -0.0905 0.6751 1.0000
4.000 0.8549 0.02571 0.01544 -0.0898 0.6570 1.0000
4.250 0.8808 0.02644 0.01618 -0.0891 0.6402 1.0000
4.500 0.9063 0.02723 0.01699 -0.0883 0.6239 1.0000
4.750 0.9309 0.02808 0.01793 -0.0874 0.6081 1.0000
5.000 0.9556 0.02892 0.01880 -0.0865 0.5920 1.0000
5.250 0.9789 0.02962 0.01953 -0.0850 0.5729 1.0000
5.500 1.0003 0.03018 0.02011 -0.0830 0.5504 1.0000
5.750 1.0253 0.03053 0.02044 -0.0812 0.5279 1.0000
6.000 1.0451 0.03128 0.02126 -0.0793 0.5064 1.0000
6.250 1.0706 0.03171 0.02166 -0.0778 0.4854 1.0000
6.500 1.0877 0.03252 0.02261 -0.0756 0.4624 1.0000
6.750 1.1117 0.03280 0.02288 -0.0738 0.4382 1.0000
7.000 1.1316 0.03317 0.02329 -0.0715 0.4112 1.0000
7.250 1.1510 0.03352 0.02361 -0.0691 0.3815 1.0000
7.500 1.1710 0.03397 0.02395 -0.0668 0.3509 1.0000
7.750 1.1886 0.03476 0.02471 -0.0644 0.3219 1.0000
8.000 1.2028 0.03612 0.02619 -0.0621 0.2977 1.0000
8.250 1.2232 0.03753 0.02759 -0.0606 0.2802 1.0000
8.500 1.2404 0.03944 0.02968 -0.0590 0.2666 1.0000
8.750 1.2554 0.04173 0.03223 -0.0573 0.2563 1.0000
9.000 1.2762 0.04359 0.03419 -0.0563 0.2475 1.0000
9.250 1.2844 0.04624 0.03725 -0.0541 0.2395 1.0000
9.500 1.2994 0.04838 0.03958 -0.0527 0.2321 1.0000
9.750 1.3032 0.05124 0.04282 -0.0503 0.2254 1.0000
10.000 1.3152 0.05310 0.04485 -0.0486 0.2169 1.0000
10.250 1.3328 0.05350 0.04527 -0.0470 0.2037 1.0000
10.500 1.3508 0.05397 0.04580 -0.0454 0.1909 1.0000
10.750 1.3363 0.05773 0.05007 -0.0419 0.1862 1.0000
11.000 1.2279 0.07291 0.06586 -0.0377 0.2104 1.0000
11.250 1.2089 0.07778 0.07081 -0.0367 0.2081 1.0000
11.500 1.1905 0.08350 0.07660 -0.0368 0.2065 1.0000
12.000 1.3530 0.06531 0.05753 -0.0285 0.1116 1.0000
12.250 1.3181 0.06961 0.06230 -0.0251 0.1136 1.0000
12.500 1.2886 0.07469 0.06768 -0.0238 0.1140 1.0000
12.750 1.2647 0.08008 0.07325 -0.0238 0.1130 1.0000
13.000 1.2429 0.08603 0.07933 -0.0249 0.1118 1.0000
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Polar data table (+)
Polar graphs
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