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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.96 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe622-il-1000000-n5.txt
Download as CSV file: xf-goe622-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5432   0.12888   0.12723   0.0048   1.0000   0.0028
 -11.250  -0.5411   0.12445   0.12280   0.0032   1.0000   0.0029
 -10.250  -0.8227   0.02976   0.02725  -0.0542   1.0000   0.0025
 -10.000  -0.8112   0.02654   0.02373  -0.0539   1.0000   0.0026
  -9.750  -0.7960   0.02430   0.02125  -0.0533   1.0000   0.0026
  -9.500  -0.7784   0.02264   0.01940  -0.0525   1.0000   0.0027
  -9.250  -0.7596   0.02123   0.01782  -0.0518   1.0000   0.0028
  -9.000  -0.7398   0.02007   0.01651  -0.0509   1.0000   0.0029
  -8.750  -0.7196   0.01899   0.01527  -0.0501   1.0000   0.0030
  -8.500  -0.6966   0.01784   0.01395  -0.0497   0.9995   0.0032
  -8.250  -0.6662   0.01664   0.01252  -0.0510   0.9975   0.0033
  -8.000  -0.6344   0.01549   0.01118  -0.0524   0.9953   0.0035
  -7.750  -0.6035   0.01452   0.01003  -0.0535   0.9918   0.0036
  -7.500  -0.5718   0.01374   0.00911  -0.0547   0.9882   0.0038
  -7.250  -0.5419   0.01277   0.00798  -0.0555   0.9829   0.0040
  -6.750  -0.4798   0.01143   0.00645  -0.0574   0.9678   0.0045
  -6.500  -0.4481   0.01095   0.00589  -0.0583   0.9560   0.0049
  -6.250  -0.4178   0.01050   0.00534  -0.0589   0.9418   0.0052
  -6.000  -0.3898   0.01012   0.00483  -0.0590   0.9283   0.0056
  -5.750  -0.3625   0.00985   0.00448  -0.0588   0.9170   0.0059
  -5.500  -0.3359   0.00940   0.00393  -0.0586   0.9066   0.0069
  -5.000  -0.2818   0.00886   0.00325  -0.0582   0.8888   0.0085
  -4.750  -0.2545   0.00866   0.00297  -0.0580   0.8813   0.0092
  -4.500  -0.2271   0.00836   0.00262  -0.0579   0.8732   0.0120
  -4.250  -0.1998   0.00815   0.00238  -0.0578   0.8655   0.0159
  -4.000  -0.1723   0.00794   0.00217  -0.0577   0.8575   0.0241
  -3.750  -0.1447   0.00776   0.00199  -0.0576   0.8503   0.0301
  -3.500  -0.1170   0.00763   0.00182  -0.0575   0.8422   0.0352
  -3.250  -0.0893   0.00747   0.00166  -0.0575   0.8337   0.0427
  -3.000  -0.0616   0.00733   0.00151  -0.0574   0.8247   0.0525
  -2.750  -0.0340   0.00718   0.00139  -0.0574   0.8151   0.0689
  -2.500  -0.0064   0.00708   0.00129  -0.0573   0.8015   0.0860
  -2.250   0.0211   0.00702   0.00120  -0.0571   0.7848   0.0954
  -2.000   0.0486   0.00701   0.00110  -0.0570   0.7636   0.1003
  -1.750   0.0762   0.00697   0.00102  -0.0569   0.7448   0.1072
  -1.500   0.1034   0.00700   0.00095  -0.0567   0.7169   0.1131
  -1.250   0.1301   0.00706   0.00088  -0.0564   0.6770   0.1228
  -1.000   0.1564   0.00719   0.00085  -0.0562   0.6290   0.1349
  -0.750   0.1831   0.00721   0.00083  -0.0560   0.5914   0.1688
  -0.500   0.2101   0.00713   0.00081  -0.0560   0.5676   0.2222
  -0.250   0.2375   0.00702   0.00080  -0.0560   0.5501   0.2807
   0.000   0.2650   0.00690   0.00081  -0.0560   0.5360   0.3425
   0.250   0.2924   0.00678   0.00082  -0.0561   0.5232   0.4052
   0.500   0.3199   0.00664   0.00083  -0.0561   0.5116   0.4764
   0.750   0.3471   0.00648   0.00086  -0.0561   0.4993   0.5576
   1.000   0.3741   0.00631   0.00090  -0.0560   0.4858   0.6436
   1.250   0.4001   0.00609   0.00096  -0.0557   0.4708   0.7505
   1.500   0.4233   0.00587   0.00104  -0.0546   0.4526   0.8680
   1.750   0.4469   0.00587   0.00112  -0.0533   0.4196   0.9533
   2.000   0.4854   0.00625   0.00122  -0.0560   0.3494   1.0000
   2.250   0.5113   0.00654   0.00134  -0.0557   0.3109   1.0000
   2.500   0.5374   0.00680   0.00146  -0.0554   0.2800   1.0000
   2.750   0.5635   0.00709   0.00160  -0.0552   0.2451   1.0000
   3.000   0.5898   0.00733   0.00173  -0.0550   0.2199   1.0000
   3.250   0.6165   0.00754   0.00187  -0.0548   0.2014   1.0000
   3.500   0.6414   0.00801   0.00208  -0.0545   0.1456   1.0000
   3.750   0.6674   0.00833   0.00228  -0.0542   0.1209   1.0000
   4.000   0.6940   0.00855   0.00246  -0.0541   0.1094   1.0000
   4.250   0.7204   0.00879   0.00265  -0.0539   0.0980   1.0000
   4.500   0.7462   0.00913   0.00285  -0.0536   0.0699   1.0000
   4.750   0.7716   0.00953   0.00314  -0.0533   0.0458   1.0000
   5.000   0.7962   0.01005   0.00350  -0.0529   0.0185   1.0000
   5.250   0.8225   0.01031   0.00377  -0.0526   0.0123   1.0000
   5.500   0.8488   0.01056   0.00405  -0.0524   0.0105   1.0000
   5.750   0.8747   0.01088   0.00440  -0.0521   0.0087   1.0000
   6.000   0.9001   0.01127   0.00483  -0.0517   0.0072   1.0000
   6.250   0.9259   0.01157   0.00518  -0.0514   0.0067   1.0000
   6.500   0.9514   0.01191   0.00555  -0.0511   0.0060   1.0000
   6.750   0.9765   0.01228   0.00594  -0.0508   0.0054   1.0000
   7.000   1.0007   0.01281   0.00650  -0.0502   0.0047   1.0000
   7.250   1.0256   0.01320   0.00695  -0.0498   0.0044   1.0000
   7.500   1.0501   0.01365   0.00745  -0.0494   0.0041   1.0000
   7.750   1.0741   0.01414   0.00799  -0.0488   0.0039   1.0000
   8.000   1.0979   0.01465   0.00857  -0.0483   0.0036   1.0000
   8.250   1.1214   0.01517   0.00915  -0.0477   0.0034   1.0000
   8.500   1.1441   0.01579   0.00982  -0.0471   0.0032   1.0000
   8.750   1.1637   0.01682   0.01095  -0.0459   0.0030   1.0000
   9.000   1.1858   0.01745   0.01165  -0.0452   0.0029   1.0000
   9.250   1.2076   0.01809   0.01238  -0.0444   0.0027   1.0000
   9.500   1.2287   0.01879   0.01316  -0.0436   0.0026   1.0000
   9.750   1.2489   0.01956   0.01402  -0.0426   0.0024   1.0000
  10.000   1.2680   0.02043   0.01498  -0.0415   0.0023   1.0000
  10.250   1.2863   0.02134   0.01599  -0.0403   0.0022   1.0000
  10.500   1.3040   0.02227   0.01702  -0.0391   0.0022   1.0000
  10.750   1.3208   0.02322   0.01810  -0.0378   0.0021   1.0000
  11.000   1.3368   0.02419   0.01917  -0.0364   0.0020   1.0000
  11.250   1.3512   0.02524   0.02032  -0.0349   0.0020   1.0000
  11.500   1.3642   0.02634   0.02153  -0.0332   0.0019   1.0000
  11.750   1.3726   0.02756   0.02287  -0.0308   0.0019   1.0000
  12.000   1.3765   0.02900   0.02443  -0.0280   0.0018   1.0000
  12.250   1.3767   0.03080   0.02639  -0.0251   0.0018   1.0000
  12.500   1.3709   0.03325   0.02903  -0.0223   0.0017   1.0000
  12.750   1.3630   0.03613   0.03211  -0.0201   0.0017   1.0000
  13.000   1.3616   0.03859   0.03473  -0.0189   0.0017   1.0000
  13.250   1.3570   0.04161   0.03791  -0.0182   0.0017   1.0000
  13.500   1.3505   0.04512   0.04159  -0.0181   0.0017   1.0000
  13.750   1.3432   0.04908   0.04573  -0.0187   0.0016   1.0000
  14.000   1.3322   0.05391   0.05074  -0.0202   0.0016   1.0000
  14.250   1.3192   0.05951   0.05651  -0.0225   0.0016   1.0000
  14.500   1.3056   0.06553   0.06268  -0.0254   0.0016   1.0000
  14.750   1.2869   0.07275   0.07007  -0.0291   0.0016   1.0000
  15.000   1.2665   0.08061   0.07809  -0.0332   0.0016   1.0000
  15.250   1.2426   0.08962   0.08725  -0.0380   0.0016   1.0000
  15.500   1.2164   0.09960   0.09737  -0.0433   0.0017   1.0000
  15.750   1.1919   0.10950   0.10740  -0.0484   0.0017   1.0000
  16.000   1.1686   0.11934   0.11735  -0.0533   0.0017   1.0000
  16.250   1.1401   0.13054   0.12865  -0.0589   0.0017   1.0000
  16.500   1.1162   0.14117   0.13938  -0.0642   0.0017   1.0000
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