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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 500,000
Max Cl/Cd: 89.15 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe122-il-500000-n5.txt
Download as CSV file: xf-goe122-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 122 (MVA H.2) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4276   0.10070   0.09853  -0.0012   1.0000   0.0073
  -8.500  -0.4229   0.09692   0.09477  -0.0032   1.0000   0.0073
  -8.250  -0.4213   0.09203   0.08992  -0.0062   1.0000   0.0077
  -8.000  -0.4127   0.08980   0.08770  -0.0074   1.0000   0.0080
  -7.750  -0.4051   0.08713   0.08506  -0.0092   1.0000   0.0082
  -7.500  -0.3976   0.08394   0.08189  -0.0119   1.0000   0.0085
  -7.250  -0.3873   0.07973   0.07770  -0.0163   1.0000   0.0085
  -7.000  -0.3662   0.07418   0.07213  -0.0243   0.9622   0.0084
  -6.750  -0.3453   0.06908   0.06695  -0.0311   0.9361   0.0085
  -6.500  -0.3267   0.06432   0.06211  -0.0365   0.9166   0.0087
  -6.250  -0.3061   0.05936   0.05704  -0.0420   0.9016   0.0090
  -6.000  -0.2825   0.05380   0.05132  -0.0478   0.8886   0.0093
  -5.500  -0.2281   0.04115   0.03823  -0.0587   0.8647   0.0109
  -5.250  -0.2023   0.03783   0.03473  -0.0607   0.8520   0.0113
  -4.750  -0.1453   0.02370   0.01952  -0.0654   0.8312   0.0143
  -4.500  -0.1194   0.02326   0.01898  -0.0654   0.8180   0.0149
  -4.250  -0.0928   0.02145   0.01689  -0.0655   0.8038   0.0159
  -4.000  -0.0651   0.01664   0.01125  -0.0654   0.7903   0.0189
  -3.750  -0.0384   0.01642   0.01092  -0.0653   0.7731   0.0195
  -3.500  -0.0115   0.01592   0.01026  -0.0652   0.7540   0.0203
  -3.250   0.0158   0.01510   0.00918  -0.0650   0.7343   0.0214
  -3.000   0.0433   0.01442   0.00822  -0.0648   0.7154   0.0230
  -2.750   0.0711   0.01388   0.00740  -0.0646   0.6971   0.0239
  -2.500   0.0989   0.01364   0.00694  -0.0644   0.6789   0.0243
  -2.250   0.1260   0.01235   0.00547  -0.0644   0.6619   0.0256
  -2.000   0.1536   0.01196   0.00496  -0.0643   0.6463   0.0266
  -1.750   0.1813   0.01155   0.00444  -0.0643   0.6323   0.0272
  -1.500   0.2090   0.01119   0.00398  -0.0642   0.6175   0.0277
  -1.250   0.2366   0.01090   0.00356  -0.0641   0.5999   0.0282
  -1.000   0.2643   0.01064   0.00320  -0.0640   0.5815   0.0286
  -0.750   0.2920   0.01045   0.00292  -0.0639   0.5629   0.0294
  -0.500   0.3198   0.01027   0.00266  -0.0638   0.5447   0.0301
  -0.250   0.3474   0.01011   0.00240  -0.0638   0.5227   0.0303
   0.000   0.3749   0.01002   0.00218  -0.0637   0.4951   0.0306
   0.250   0.4025   0.00999   0.00202  -0.0636   0.4692   0.0310
   0.500   0.4301   0.00997   0.00191  -0.0636   0.4505   0.0315
   0.750   0.4579   0.00996   0.00183  -0.0636   0.4367   0.0320
   1.000   0.4857   0.00993   0.00175  -0.0636   0.4257   0.0326
   1.250   0.5136   0.00992   0.00168  -0.0636   0.4164   0.0337
   1.500   0.5415   0.00994   0.00166  -0.0636   0.4078   0.0347
   1.750   0.5693   0.00997   0.00166  -0.0636   0.4004   0.0368
   2.000   0.5971   0.01002   0.00169  -0.0636   0.3914   0.0387
   2.250   0.6249   0.01008   0.00173  -0.0636   0.3828   0.0402
   2.750   0.6765   0.00828   0.00203  -0.0633   0.3581   1.0000
   3.000   0.7039   0.00845   0.00211  -0.0633   0.3448   1.0000
   3.250   0.7315   0.00858   0.00220  -0.0632   0.3356   1.0000
   3.500   0.7588   0.00877   0.00232  -0.0632   0.3208   1.0000
   3.750   0.7859   0.00897   0.00244  -0.0631   0.3047   1.0000
   4.000   0.8131   0.00917   0.00258  -0.0630   0.2902   1.0000
   4.250   0.8398   0.00942   0.00275  -0.0630   0.2705   1.0000
   4.500   0.8662   0.00975   0.00295  -0.0629   0.2421   1.0000
   4.750   0.8912   0.01030   0.00326  -0.0627   0.1940   1.0000
   5.000   0.9168   0.01075   0.00359  -0.0625   0.1717   1.0000
   5.250   0.9429   0.01110   0.00389  -0.0623   0.1594   1.0000
   5.500   0.9693   0.01139   0.00417  -0.0622   0.1493   1.0000
   5.750   0.9949   0.01178   0.00450  -0.0620   0.1319   1.0000
   6.000   1.0159   0.01298   0.00525  -0.0614   0.0503   1.0000
   6.250   1.0409   0.01344   0.00570  -0.0611   0.0408   1.0000
   6.500   1.0663   0.01384   0.00612  -0.0609   0.0378   1.0000
   6.750   1.0914   0.01426   0.00660  -0.0605   0.0348   1.0000
   7.000   1.1164   0.01467   0.00707  -0.0602   0.0328   1.0000
   7.250   1.1415   0.01503   0.00749  -0.0600   0.0317   1.0000
   7.500   1.1663   0.01542   0.00796  -0.0597   0.0301   1.0000
   7.750   1.1906   0.01587   0.00848  -0.0593   0.0281   1.0000
   8.000   1.2141   0.01641   0.00906  -0.0589   0.0258   1.0000
   8.250   1.2363   0.01712   0.00984  -0.0583   0.0232   1.0000
   8.500   1.2610   0.01742   0.01019  -0.0580   0.0219   1.0000
   8.750   1.2849   0.01781   0.01064  -0.0576   0.0191   1.0000
   9.000   1.3075   0.01835   0.01119  -0.0571   0.0163   1.0000
   9.250   1.3295   0.01894   0.01184  -0.0565   0.0143   1.0000
   9.500   1.3509   0.01957   0.01246  -0.0559   0.0123   1.0000
   9.750   1.3706   0.02035   0.01329  -0.0550   0.0107   1.0000
  10.000   1.3901   0.02110   0.01414  -0.0541   0.0097   1.0000
  10.250   1.4084   0.02193   0.01506  -0.0531   0.0089   1.0000
  10.500   1.4247   0.02291   0.01611  -0.0519   0.0082   1.0000
  10.750   1.4383   0.02405   0.01736  -0.0504   0.0076   1.0000
  11.000   1.4522   0.02507   0.01850  -0.0489   0.0072   1.0000
  11.250   1.4637   0.02616   0.01971  -0.0472   0.0068   1.0000
  11.500   1.4716   0.02727   0.02092  -0.0449   0.0064   1.0000
  11.750   1.4783   0.02855   0.02230  -0.0430   0.0061   1.0000
  12.000   1.4832   0.03008   0.02394  -0.0412   0.0058   1.0000
  12.250   1.4844   0.03209   0.02607  -0.0396   0.0056   1.0000
  12.500   1.4824   0.03460   0.02870  -0.0384   0.0054   1.0000
  12.750   1.4838   0.03697   0.03122  -0.0377   0.0053   1.0000
  13.000   1.4836   0.03971   0.03410  -0.0373   0.0052   1.0000
  13.250   1.4822   0.04277   0.03731  -0.0373   0.0050   1.0000
  13.500   1.4792   0.04620   0.04089  -0.0377   0.0049   1.0000
  13.750   1.4750   0.04994   0.04478  -0.0383   0.0048   1.0000
  14.000   1.4695   0.05399   0.04896  -0.0392   0.0047   1.0000
  14.250   1.4626   0.05830   0.05342  -0.0403   0.0047   1.0000
  14.500   1.4547   0.06286   0.05812  -0.0415   0.0046   1.0000
  14.750   1.4456   0.06765   0.06305  -0.0429   0.0045   1.0000
  15.000   1.4360   0.07264   0.06817  -0.0445   0.0044   1.0000
  15.250   1.4257   0.07786   0.07352  -0.0462   0.0044   1.0000
  15.500   1.4153   0.08320   0.07899  -0.0481   0.0043   1.0000
  15.750   1.4046   0.08869   0.08461  -0.0501   0.0043   1.0000
  16.000   1.3934   0.09438   0.09043  -0.0522   0.0043   1.0000
  16.250   1.3820   0.10017   0.09634  -0.0544   0.0042   1.0000
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