GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 50,000 Max Cl/Cd: 36.38 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe563-il-50000-n5.txt Download as CSV file: xf-goe563-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 563 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4770 0.09529 0.08793 -0.0353 1.0000 0.0718
-9.000 -0.4801 0.09128 0.08399 -0.0367 1.0000 0.0717
-8.750 -0.4838 0.08738 0.08017 -0.0378 1.0000 0.0713
-8.500 -0.4898 0.08355 0.07641 -0.0387 1.0000 0.0708
-8.250 -0.4963 0.07933 0.07226 -0.0401 1.0000 0.0702
-8.000 -0.5028 0.07500 0.06795 -0.0415 1.0000 0.0697
-7.750 -0.5100 0.07052 0.06346 -0.0425 1.0000 0.0694
-7.500 -0.5168 0.06605 0.05892 -0.0432 1.0000 0.0696
-7.250 -0.5222 0.06159 0.05431 -0.0435 1.0000 0.0702
-7.000 -0.5266 0.05697 0.04940 -0.0435 1.0000 0.0712
-6.750 -0.5275 0.05253 0.04454 -0.0430 1.0000 0.0720
-6.500 -0.5220 0.04887 0.04056 -0.0420 1.0000 0.0728
-6.250 -0.5121 0.04595 0.03739 -0.0407 1.0000 0.0735
-6.000 -0.5004 0.04330 0.03451 -0.0394 1.0000 0.0745
-5.750 -0.4869 0.04117 0.03218 -0.0382 1.0000 0.0765
-5.500 -0.4725 0.03908 0.02977 -0.0370 1.0000 0.0798
-5.250 -0.4567 0.03665 0.02686 -0.0358 1.0000 0.0824
-5.000 -0.4389 0.03429 0.02400 -0.0346 1.0000 0.0838
-4.750 -0.4195 0.03221 0.02140 -0.0334 1.0000 0.0853
-4.500 -0.4000 0.03060 0.01963 -0.0324 1.0000 0.0873
-4.250 -0.3797 0.02929 0.01815 -0.0313 1.0000 0.0898
-4.000 -0.3591 0.02825 0.01689 -0.0302 1.0000 0.0948
-3.750 -0.3374 0.02718 0.01551 -0.0291 1.0000 0.1002
-3.500 -0.3164 0.02619 0.01449 -0.0282 1.0000 0.1048
-3.250 -0.2943 0.02528 0.01343 -0.0271 1.0000 0.1101
-3.000 -0.2716 0.02445 0.01246 -0.0261 1.0000 0.1164
-2.750 -0.2492 0.02376 0.01172 -0.0253 1.0000 0.1265
-2.500 -0.2274 0.02321 0.01112 -0.0245 1.0000 0.1424
-2.250 -0.2057 0.02266 0.01062 -0.0237 1.0000 0.1619
-2.000 -0.1841 0.02214 0.01017 -0.0230 1.0000 0.1914
-1.750 -0.1624 0.02150 0.00978 -0.0225 1.0000 0.2374
-1.500 -0.1325 0.02035 0.00969 -0.0238 0.9955 0.4049
-1.250 -0.0807 0.01871 0.00977 -0.0267 0.9936 1.0000
-1.000 -0.0427 0.01905 0.00969 -0.0293 0.9859 1.0000
-0.750 -0.0062 0.01936 0.00969 -0.0315 0.9776 1.0000
-0.500 0.0296 0.01969 0.00976 -0.0337 0.9693 1.0000
-0.250 0.0679 0.02005 0.00989 -0.0362 0.9616 1.0000
0.000 0.1011 0.02033 0.01000 -0.0377 0.9520 1.0000
0.250 0.1355 0.02063 0.01016 -0.0395 0.9427 1.0000
0.500 0.1736 0.02095 0.01036 -0.0418 0.9343 1.0000
0.750 0.2051 0.02121 0.01054 -0.0429 0.9235 1.0000
1.000 0.2397 0.02147 0.01074 -0.0445 0.9132 1.0000
1.250 0.2809 0.02167 0.01090 -0.0471 0.9030 1.0000
1.500 0.3204 0.02172 0.01095 -0.0492 0.8892 1.0000
1.750 0.3609 0.02167 0.01091 -0.0511 0.8744 1.0000
2.000 0.3987 0.02160 0.01089 -0.0526 0.8597 1.0000
2.250 0.4327 0.02157 0.01089 -0.0532 0.8453 1.0000
2.500 0.4655 0.02152 0.01091 -0.0537 0.8306 1.0000
2.750 0.4951 0.02149 0.01096 -0.0534 0.8141 1.0000
3.000 0.5241 0.02144 0.01100 -0.0530 0.7966 1.0000
3.250 0.5539 0.02135 0.01101 -0.0526 0.7785 1.0000
3.500 0.5851 0.02120 0.01098 -0.0523 0.7596 1.0000
3.750 0.6148 0.02106 0.01095 -0.0517 0.7385 1.0000
4.000 0.6429 0.02095 0.01097 -0.0507 0.7143 1.0000
4.250 0.6702 0.02084 0.01094 -0.0496 0.6854 1.0000
4.500 0.6969 0.02069 0.01082 -0.0481 0.6484 1.0000
4.750 0.7219 0.02066 0.01076 -0.0463 0.6045 1.0000
5.000 0.7452 0.02081 0.01082 -0.0445 0.5569 1.0000
5.250 0.7675 0.02115 0.01103 -0.0427 0.5103 1.0000
5.500 0.7884 0.02167 0.01140 -0.0410 0.4661 1.0000
5.750 0.8081 0.02231 0.01193 -0.0392 0.4246 1.0000
6.000 0.8272 0.02306 0.01257 -0.0375 0.3871 1.0000
6.250 0.8457 0.02392 0.01328 -0.0358 0.3530 1.0000
6.500 0.8643 0.02484 0.01413 -0.0343 0.3209 1.0000
6.750 0.8820 0.02582 0.01506 -0.0327 0.2886 1.0000
7.000 0.8963 0.02678 0.01596 -0.0307 0.2521 1.0000
7.250 0.9090 0.02776 0.01679 -0.0287 0.2171 1.0000
7.500 0.9236 0.02880 0.01779 -0.0269 0.1868 1.0000
7.750 0.9387 0.02999 0.01895 -0.0253 0.1615 1.0000
8.000 0.9540 0.03140 0.02035 -0.0237 0.1385 1.0000
8.250 0.9675 0.03298 0.02186 -0.0220 0.1191 1.0000
8.500 0.9824 0.03468 0.02352 -0.0204 0.1040 1.0000
8.750 1.0006 0.03645 0.02543 -0.0191 0.0924 1.0000
9.000 1.0172 0.03819 0.02735 -0.0177 0.0827 1.0000
9.250 1.0325 0.03998 0.02912 -0.0164 0.0762 1.0000
9.500 1.0496 0.04204 0.03153 -0.0150 0.0698 1.0000
9.750 1.0616 0.04379 0.03323 -0.0136 0.0650 1.0000
10.000 1.0759 0.04642 0.03635 -0.0121 0.0610 1.0000
10.250 1.0858 0.04894 0.03916 -0.0104 0.0576 1.0000
10.500 1.0927 0.05102 0.04133 -0.0086 0.0547 1.0000
10.750 1.0956 0.05374 0.04424 -0.0066 0.0524 1.0000
11.000 1.0912 0.05699 0.04792 -0.0042 0.0509 1.0000
11.250 1.0835 0.06055 0.05184 -0.0021 0.0500 1.0000
11.500 1.0714 0.06439 0.05600 -0.0005 0.0494 1.0000
11.750 1.0555 0.06863 0.06053 0.0004 0.0490 1.0000
12.000 1.0358 0.07353 0.06568 0.0002 0.0488 1.0000
12.250 1.0125 0.07931 0.07170 -0.0014 0.0489 1.0000
12.500 0.9861 0.08633 0.07891 -0.0047 0.0495 1.0000
12.750 0.9563 0.09511 0.08784 -0.0100 0.0502 1.0000
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Polar data table (+)
Polar graphs
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