GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 10K AIRFOIL (goe10k-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.96 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe10k-il-1000000-n5.txt Download as CSV file: xf-goe10k-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 10K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5371 0.09005 0.08844 -0.0084 1.0000 0.0028
-7.750 -0.5397 0.08692 0.08534 -0.0089 1.0000 0.0029
-7.500 -0.5451 0.08444 0.08289 -0.0086 1.0000 0.0028
-7.250 -0.5441 0.08042 0.07889 -0.0112 1.0000 0.0029
-7.000 -0.5405 0.07679 0.07526 -0.0135 1.0000 0.0029
-6.750 -0.5346 0.07249 0.07096 -0.0165 1.0000 0.0029
-6.500 -0.5271 0.06834 0.06679 -0.0191 1.0000 0.0029
-6.250 -0.5129 0.06348 0.06189 -0.0229 0.9997 0.0029
-6.000 -0.4858 0.05736 0.05567 -0.0294 0.9982 0.0029
-5.750 -0.4583 0.05176 0.04996 -0.0347 0.9966 0.0029
-5.500 -0.4296 0.04628 0.04432 -0.0391 0.9953 0.0029
-5.000 -0.3763 0.03470 0.03230 -0.0448 0.9908 0.0017
-4.750 -0.3472 0.02927 0.02657 -0.0464 0.9889 0.0016
-4.500 -0.3177 0.02412 0.02106 -0.0473 0.9875 0.0016
-4.250 -0.2933 0.01833 0.01476 -0.0459 0.9844 0.0016
-4.000 -0.2688 0.01267 0.00832 -0.0441 0.9818 0.0018
-3.750 -0.2407 0.01110 0.00643 -0.0441 0.9803 0.0020
-3.500 -0.2112 0.01033 0.00549 -0.0445 0.9792 0.0026
-3.250 -0.1822 0.00915 0.00406 -0.0447 0.9782 0.0027
-3.000 -0.1567 0.00836 0.00311 -0.0440 0.9756 0.0029
-2.750 -0.1308 0.00774 0.00240 -0.0436 0.9726 0.0035
-2.500 -0.1020 0.00739 0.00197 -0.0438 0.9706 0.0043
-2.250 -0.0722 0.00709 0.00164 -0.0443 0.9690 0.0063
-2.000 -0.0418 0.00680 0.00133 -0.0450 0.9677 0.0119
-1.750 -0.0104 0.00648 0.00111 -0.0459 0.9664 0.0459
-1.500 0.0126 0.00632 0.00098 -0.0448 0.9596 0.0625
-1.250 0.0447 0.00602 0.00083 -0.0459 0.9550 0.1052
-1.000 0.0764 0.00573 0.00069 -0.0469 0.9469 0.1690
-0.750 0.1135 0.00536 0.00057 -0.0493 0.9388 0.2611
-0.500 0.1461 0.00500 0.00048 -0.0506 0.9279 0.3722
-0.250 0.1774 0.00456 0.00042 -0.0517 0.9144 0.5156
0.000 0.2040 0.00411 0.00040 -0.0516 0.8961 0.6762
0.250 0.2240 0.00371 0.00041 -0.0497 0.8680 0.8304
0.750 0.3176 0.00524 0.00070 -0.0589 0.4517 0.9984
1.000 0.3446 0.00569 0.00081 -0.0591 0.3518 1.0000
1.250 0.3644 0.00620 0.00092 -0.0576 0.2349 1.0000
1.500 0.3852 0.00667 0.00107 -0.0562 0.1389 1.0000
1.750 0.4066 0.00711 0.00125 -0.0550 0.0661 1.0000
2.000 0.4305 0.00729 0.00139 -0.0542 0.0507 1.0000
2.250 0.4529 0.00767 0.00160 -0.0531 0.0108 1.0000
2.500 0.4765 0.00793 0.00190 -0.0522 0.0062 1.0000
2.750 0.4999 0.00823 0.00223 -0.0512 0.0043 1.0000
3.000 0.5230 0.00858 0.00264 -0.0502 0.0036 1.0000
3.250 0.5450 0.00913 0.00327 -0.0488 0.0031 1.0000
3.500 0.5686 0.00942 0.00360 -0.0479 0.0023 1.0000
3.750 0.5896 0.01017 0.00446 -0.0464 0.0019 1.0000
4.000 0.6105 0.01112 0.00558 -0.0447 0.0018 1.0000
4.250 0.6309 0.01273 0.00745 -0.0426 0.0017 1.0000
4.500 0.6519 0.01517 0.01027 -0.0404 0.0017 1.0000
4.750 0.6717 0.01832 0.01384 -0.0377 0.0017 1.0000
5.000 0.6892 0.02171 0.01764 -0.0349 0.0019 1.0000
5.500 0.7123 0.03094 0.02767 -0.0277 0.0033 1.0000
5.750 0.7334 0.03514 0.03213 -0.0247 0.0024 1.0000
6.000 0.7477 0.03761 0.03477 -0.0232 0.0021 1.0000
7.500 0.7323 0.05449 0.05290 -0.0120 0.0020 1.0000
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Polar data table (+)
Polar graphs
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