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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 100,000
Max Cl/Cd: 53.25 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe622-il-100000.txt
Download as CSV file: xf-goe622-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4956   0.10711   0.10216  -0.0099   1.0000   0.0897
  -8.750  -0.5095   0.10477   0.09994  -0.0170   1.0000   0.0912
  -8.500  -0.5215   0.10140   0.09669  -0.0257   1.0000   0.0916
  -8.250  -0.4863   0.09550   0.09068  -0.0136   1.0000   0.0958
  -8.000  -0.4825   0.09228   0.08750  -0.0147   1.0000   0.1005
  -7.750  -0.4909   0.08887   0.08420  -0.0208   1.0000   0.1041
  -7.500  -0.5010   0.08437   0.07959  -0.0353   1.0000   0.1056
  -7.250  -0.4801   0.08062   0.07602  -0.0229   1.0000   0.1103
  -7.000  -0.4741   0.07685   0.07226  -0.0256   1.0000   0.1154
  -6.500  -0.4638   0.06797   0.06335  -0.0322   1.0000   0.1237
  -6.250  -0.4544   0.06451   0.05987  -0.0328   1.0000   0.1291
  -6.000  -0.4481   0.05979   0.05500  -0.0367   1.0000   0.1364
  -5.750  -0.4363   0.05668   0.05191  -0.0354   1.0000   0.1406
  -5.500  -0.4176   0.04240   0.03624  -0.0430   1.0000   0.0776
  -5.250  -0.4027   0.03824   0.03203  -0.0422   1.0000   0.0742
  -5.000  -0.3855   0.03424   0.02755  -0.0415   1.0000   0.0739
  -4.750  -0.3661   0.03059   0.02336  -0.0406   1.0000   0.0739
  -4.500  -0.3444   0.02728   0.01945  -0.0396   1.0000   0.0739
  -4.250  -0.3209   0.02483   0.01635  -0.0385   1.0000   0.0771
  -4.000  -0.2989   0.02329   0.01474  -0.0378   1.0000   0.0847
  -3.750  -0.2737   0.02177   0.01266  -0.0368   1.0000   0.0916
  -3.500  -0.2502   0.02059   0.01144  -0.0362   1.0000   0.1044
  -3.250  -0.2255   0.01936   0.01014  -0.0356   1.0000   0.1181
  -3.000  -0.2005   0.01825   0.00900  -0.0352   1.0000   0.1364
  -2.750  -0.1755   0.01735   0.00814  -0.0348   1.0000   0.1613
  -2.500  -0.1500   0.01645   0.00741  -0.0346   1.0000   0.1932
  -2.250  -0.1247   0.01578   0.00694  -0.0345   1.0000   0.2313
  -2.000  -0.0992   0.01515   0.00657  -0.0344   1.0000   0.2798
  -1.750  -0.0718   0.01374   0.00629  -0.0349   1.0000   0.4788
  -1.500  -0.0489   0.01245   0.00626  -0.0320   1.0000   1.0000
  -1.250  -0.0267   0.01266   0.00619  -0.0316   1.0000   1.0000
  -1.000  -0.0047   0.01291   0.00621  -0.0312   1.0000   1.0000
  -0.750   0.0170   0.01321   0.00634  -0.0309   1.0000   1.0000
  -0.500   0.0383   0.01358   0.00657  -0.0307   1.0000   1.0000
  -0.250   0.0883   0.01394   0.00676  -0.0359   0.9898   1.0000
   0.000   0.1388   0.01426   0.00693  -0.0410   0.9784   1.0000
   0.250   0.1886   0.01451   0.00709  -0.0459   0.9667   1.0000
   0.500   0.2385   0.01468   0.00719  -0.0507   0.9547   1.0000
   0.750   0.2893   0.01475   0.00723  -0.0554   0.9431   1.0000
   1.000   0.3382   0.01473   0.00720  -0.0596   0.9298   1.0000
   1.250   0.3864   0.01455   0.00704  -0.0631   0.9154   1.0000
   1.500   0.4272   0.01436   0.00686  -0.0649   0.8980   1.0000
   1.750   0.4622   0.01424   0.00676  -0.0655   0.8797   1.0000
   2.000   0.4944   0.01416   0.00672  -0.0656   0.8625   1.0000
   2.250   0.5245   0.01407   0.00664  -0.0651   0.8449   1.0000
   2.500   0.5502   0.01406   0.00664  -0.0638   0.8244   1.0000
   2.750   0.5760   0.01399   0.00658  -0.0624   0.8037   1.0000
   3.000   0.6007   0.01395   0.00657  -0.0609   0.7816   1.0000
   3.250   0.6258   0.01390   0.00651  -0.0594   0.7596   1.0000
   3.500   0.6500   0.01393   0.00655  -0.0579   0.7352   1.0000
   3.750   0.6747   0.01397   0.00662  -0.0565   0.7111   1.0000
   4.000   0.7000   0.01406   0.00670  -0.0553   0.6877   1.0000
   4.250   0.7244   0.01423   0.00688  -0.0540   0.6612   1.0000
   4.500   0.7486   0.01444   0.00706  -0.0527   0.6323   1.0000
   4.750   0.7721   0.01470   0.00733  -0.0513   0.5991   1.0000
   5.000   0.7949   0.01499   0.00758  -0.0497   0.5612   1.0000
   5.250   0.8168   0.01534   0.00785  -0.0481   0.5171   1.0000
   5.500   0.8375   0.01573   0.00816  -0.0463   0.4617   1.0000
   5.750   0.8568   0.01628   0.00849  -0.0445   0.3945   1.0000
   6.000   0.8745   0.01717   0.00901  -0.0427   0.3261   1.0000
   6.250   0.8929   0.01818   0.00972  -0.0413   0.2735   1.0000
   6.500   0.9126   0.01913   0.01051  -0.0401   0.2343   1.0000
   6.750   0.9326   0.01991   0.01123  -0.0391   0.1880   1.0000
   7.000   0.9476   0.02152   0.01247  -0.0375   0.1198   1.0000
   7.250   0.9602   0.02382   0.01437  -0.0350   0.0734   1.0000
   7.500   0.9759   0.02563   0.01606  -0.0333   0.0608   1.0000
   7.750   0.9955   0.02736   0.01795  -0.0316   0.0551   1.0000
   8.000   1.0155   0.02939   0.01997  -0.0303   0.0511   1.0000
   8.250   1.0382   0.03254   0.02315  -0.0294   0.0485   1.0000
   8.500   1.0597   0.03456   0.02556  -0.0281   0.0460   1.0000
   8.750   1.0792   0.03696   0.02828  -0.0268   0.0435   1.0000
   9.000   1.0965   0.04011   0.03184  -0.0253   0.0428   1.0000
   9.250   1.1090   0.04375   0.03602  -0.0234   0.0428   1.0000
   9.500   1.1154   0.04789   0.04071  -0.0211   0.0433   1.0000
   9.750   1.1159   0.05240   0.04575  -0.0187   0.0441   1.0000
  10.000   1.1111   0.05704   0.05083  -0.0163   0.0451   1.0000
  10.250   1.1021   0.06164   0.05578  -0.0141   0.0460   1.0000
  10.500   1.0893   0.06610   0.06050  -0.0121   0.0468   1.0000
  10.750   1.0729   0.07035   0.06495  -0.0102   0.0474   1.0000
  11.000   1.0564   0.07510   0.06984  -0.0094   0.0481   1.0000
  11.250   1.0515   0.07965   0.07452  -0.0092   0.0496   1.0000
  11.500   1.0194   0.08498   0.08013  -0.0118   0.0503   1.0000
  11.750   0.8759   0.08249   0.07780  -0.0041   0.0478   1.0000
  12.000   0.8503   0.08963   0.08501  -0.0071   0.0483   1.0000
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