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GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
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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