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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 50,000
Max Cl/Cd: 38.23 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe622-il-50000-n5.txt
Download as CSV file: xf-goe622-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 622 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4890   0.09974   0.09287  -0.0197   1.0000   0.0452
  -8.500  -0.4857   0.09578   0.08896  -0.0207   1.0000   0.0446
  -8.250  -0.4847   0.09173   0.08498  -0.0225   1.0000   0.0442
  -8.000  -0.4849   0.08753   0.08086  -0.0250   1.0000   0.0440
  -7.750  -0.4832   0.08286   0.07624  -0.0285   1.0000   0.0439
  -7.500  -0.4804   0.07792   0.07134  -0.0322   1.0000   0.0439
  -7.250  -0.4768   0.07277   0.06618  -0.0358   1.0000   0.0440
  -7.000  -0.4723   0.06749   0.06084  -0.0390   1.0000   0.0441
  -6.750  -0.4669   0.06215   0.05536  -0.0417   1.0000   0.0444
  -6.500  -0.4597   0.05695   0.04995  -0.0436   1.0000   0.0447
  -6.250  -0.4505   0.05192   0.04461  -0.0448   1.0000   0.0449
  -6.000  -0.4391   0.04704   0.03933  -0.0455   1.0000   0.0452
  -5.750  -0.4249   0.04233   0.03407  -0.0457   1.0000   0.0458
  -5.500  -0.4092   0.03932   0.03089  -0.0454   1.0000   0.0481
  -5.250  -0.3911   0.03720   0.02855  -0.0448   1.0000   0.0527
  -5.000  -0.3706   0.03373   0.02442  -0.0443   1.0000   0.0567
  -4.750  -0.3483   0.03050   0.02056  -0.0436   1.0000   0.0602
  -4.500  -0.3272   0.02920   0.01907  -0.0429   1.0000   0.0692
  -4.250  -0.3042   0.02732   0.01686  -0.0421   1.0000   0.0773
  -4.000  -0.2814   0.02609   0.01538  -0.0413   1.0000   0.0908
  -3.750  -0.2576   0.02468   0.01372  -0.0404   1.0000   0.1037
  -3.500  -0.2333   0.02343   0.01227  -0.0396   1.0000   0.1175
  -3.250  -0.2099   0.02262   0.01134  -0.0390   1.0000   0.1394
  -3.000  -0.1856   0.02173   0.01033  -0.0383   1.0000   0.1591
  -2.750  -0.1616   0.02105   0.00961  -0.0378   1.0000   0.1864
  -2.500  -0.1377   0.02040   0.00902  -0.0375   1.0000   0.2176
  -2.250  -0.1136   0.01975   0.00849  -0.0372   1.0000   0.2597
  -2.000  -0.0894   0.01895   0.00807  -0.0370   1.0000   0.3325
  -1.750  -0.0685   0.01763   0.00784  -0.0358   1.0000   0.5470
  -1.500  -0.0432   0.01664   0.00768  -0.0338   1.0000   1.0000
  -1.250  -0.0216   0.01682   0.00748  -0.0332   1.0000   1.0000
  -1.000  -0.0001   0.01704   0.00740  -0.0327   1.0000   1.0000
  -0.750   0.0385   0.01731   0.00736  -0.0355   0.9913   1.0000
  -0.500   0.0803   0.01758   0.00735  -0.0389   0.9802   1.0000
  -0.250   0.1212   0.01783   0.00738  -0.0420   0.9686   1.0000
   0.000   0.1613   0.01806   0.00743  -0.0449   0.9565   1.0000
   0.250   0.2006   0.01827   0.00752  -0.0476   0.9441   1.0000
   0.500   0.2404   0.01848   0.00763  -0.0503   0.9318   1.0000
   0.750   0.2807   0.01866   0.00774  -0.0530   0.9198   1.0000
   1.000   0.3205   0.01882   0.00786  -0.0555   0.9077   1.0000
   1.250   0.3585   0.01896   0.00800  -0.0575   0.8948   1.0000
   1.500   0.3938   0.01910   0.00815  -0.0589   0.8806   1.0000
   1.750   0.4268   0.01924   0.00831  -0.0597   0.8650   1.0000
   2.000   0.4586   0.01936   0.00848  -0.0602   0.8480   1.0000
   2.250   0.4902   0.01941   0.00858  -0.0604   0.8302   1.0000
   2.500   0.5212   0.01941   0.00863  -0.0603   0.8118   1.0000
   2.750   0.5477   0.01950   0.00881  -0.0595   0.7903   1.0000
   3.000   0.5762   0.01952   0.00890  -0.0589   0.7708   1.0000
   3.250   0.6022   0.01963   0.00909  -0.0580   0.7499   1.0000
   3.500   0.6289   0.01973   0.00931  -0.0571   0.7295   1.0000
   3.750   0.6553   0.01984   0.00951  -0.0561   0.7081   1.0000
   4.000   0.6815   0.01991   0.00966  -0.0550   0.6842   1.0000
   4.250   0.7064   0.01998   0.00982  -0.0535   0.6554   1.0000
   4.500   0.7300   0.02012   0.00997  -0.0518   0.6213   1.0000
   4.750   0.7533   0.02034   0.01020  -0.0501   0.5859   1.0000
   5.000   0.7768   0.02067   0.01057  -0.0487   0.5532   1.0000
   5.250   0.7996   0.02109   0.01114  -0.0474   0.5194   1.0000
   5.500   0.8221   0.02154   0.01170  -0.0460   0.4836   1.0000
   5.750   0.8433   0.02206   0.01230  -0.0445   0.4418   1.0000
   6.000   0.8637   0.02268   0.01292  -0.0429   0.3966   1.0000
   6.250   0.8835   0.02348   0.01365  -0.0414   0.3534   1.0000
   6.500   0.9012   0.02450   0.01451  -0.0397   0.3058   1.0000
   6.750   0.9157   0.02571   0.01551  -0.0380   0.2507   1.0000
   7.000   0.9323   0.02690   0.01665  -0.0367   0.2066   1.0000
   7.250   0.9467   0.02829   0.01781  -0.0354   0.1475   1.0000
   7.500   0.9594   0.03025   0.01951  -0.0339   0.0952   1.0000
   7.750   0.9719   0.03243   0.02149  -0.0321   0.0629   1.0000
   8.000   0.9839   0.03458   0.02362  -0.0303   0.0505   1.0000
   8.250   0.9956   0.03679   0.02595  -0.0284   0.0449   1.0000
   8.500   1.0095   0.03889   0.02829  -0.0265   0.0410   1.0000
   8.750   1.0216   0.04108   0.03057  -0.0249   0.0378   1.0000
   9.000   1.0368   0.04338   0.03318  -0.0233   0.0348   1.0000
   9.250   1.0506   0.04579   0.03600  -0.0218   0.0323   1.0000
   9.500   1.0629   0.04846   0.03892  -0.0203   0.0310   1.0000
   9.750   1.0729   0.05138   0.04208  -0.0188   0.0301   1.0000
  10.000   1.0803   0.05466   0.04558  -0.0173   0.0294   1.0000
  10.250   1.0817   0.05820   0.04949  -0.0155   0.0291   1.0000
  10.500   1.0765   0.06182   0.05350  -0.0135   0.0288   1.0000
  10.750   1.0670   0.06569   0.05771  -0.0121   0.0287   1.0000
  11.000   1.0543   0.06992   0.06224  -0.0115   0.0286   1.0000
  11.250   1.0392   0.07463   0.06722  -0.0121   0.0285   1.0000
  11.500   1.0228   0.07992   0.07274  -0.0137   0.0286   1.0000
  11.750   1.0058   0.08584   0.07885  -0.0165   0.0288   1.0000
  12.000   0.9886   0.09244   0.08560  -0.0202   0.0290   1.0000
  12.250   0.9721   0.09957   0.09285  -0.0245   0.0292   1.0000
  12.500   0.9414   0.11172   0.10524  -0.0332   0.0304   1.0000
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