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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 200,000
Max Cl/Cd: 72.33 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe122-il-200000-n5.txt
Download as CSV file: xf-goe122-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3928   0.09531   0.09198  -0.0079   1.0000   0.0201
  -7.750  -0.3869   0.09208   0.08879  -0.0098   1.0000   0.0204
  -7.500  -0.3814   0.08885   0.08560  -0.0118   1.0000   0.0208
  -7.250  -0.3742   0.08546   0.08224  -0.0146   1.0000   0.0211
  -7.000  -0.3640   0.08178   0.07860  -0.0182   1.0000   0.0215
  -6.750  -0.3481   0.07774   0.07456  -0.0253   1.0000   0.0236
  -6.500  -0.3290   0.07321   0.07000  -0.0328   1.0000   0.0240
  -6.250  -0.3125   0.06895   0.06571  -0.0374   1.0000   0.0241
  -5.750  -0.2690   0.05970   0.05638  -0.0452   0.9807   0.0235
  -5.500  -0.2413   0.05463   0.05122  -0.0504   0.9670   0.0211
  -5.250  -0.2055   0.04870   0.04509  -0.0575   0.9532   0.0204
  -5.000  -0.1706   0.04409   0.04025  -0.0625   0.9392   0.0224
  -4.750  -0.1366   0.03875   0.03457  -0.0667   0.9253   0.0231
  -4.500  -0.1058   0.03381   0.02923  -0.0690   0.9118   0.0234
  -4.250  -0.0778   0.02981   0.02478  -0.0702   0.8992   0.0253
  -4.000  -0.0540   0.02888   0.02377  -0.0704   0.8864   0.0275
  -3.750  -0.0265   0.02589   0.02036  -0.0706   0.8745   0.0283
  -3.500   0.0009   0.02330   0.01730  -0.0704   0.8625   0.0293
  -3.250   0.0292   0.02184   0.01531  -0.0699   0.8496   0.0319
  -3.000   0.0561   0.01986   0.01290  -0.0696   0.8363   0.0325
  -2.750   0.0824   0.01810   0.01084  -0.0693   0.8222   0.0335
  -2.500   0.1085   0.01727   0.00990  -0.0691   0.8071   0.0356
  -2.250   0.1355   0.01633   0.00872  -0.0686   0.7914   0.0366
  -2.000   0.1626   0.01546   0.00759  -0.0681   0.7748   0.0371
  -1.750   0.1897   0.01473   0.00666  -0.0676   0.7570   0.0377
  -1.500   0.2166   0.01416   0.00591  -0.0671   0.7390   0.0385
  -1.250   0.2436   0.01375   0.00534  -0.0667   0.7210   0.0403
  -1.000   0.2704   0.01331   0.00476  -0.0662   0.7030   0.0408
  -0.750   0.2972   0.01291   0.00425  -0.0658   0.6850   0.0410
  -0.500   0.3241   0.01258   0.00383  -0.0655   0.6671   0.0413
  -0.250   0.3511   0.01233   0.00349  -0.0652   0.6502   0.0418
   0.000   0.3783   0.01215   0.00321  -0.0649   0.6335   0.0423
   0.250   0.4053   0.01198   0.00293  -0.0647   0.6153   0.0435
   0.500   0.4324   0.01190   0.00273  -0.0644   0.5963   0.0451
   0.750   0.4597   0.01186   0.00262  -0.0642   0.5761   0.0486
   1.000   0.4868   0.01188   0.00253  -0.0640   0.5553   0.0524
   1.250   0.5140   0.01191   0.00247  -0.0638   0.5354   0.0565
   1.500   0.5412   0.01188   0.00247  -0.0637   0.5152   0.0879
   1.750   0.5668   0.00992   0.00256  -0.0634   0.4968   1.0000
   2.000   0.5936   0.01013   0.00259  -0.0631   0.4795   1.0000
   2.250   0.6205   0.01034   0.00265  -0.0629   0.4648   1.0000
   2.500   0.6474   0.01054   0.00274  -0.0627   0.4518   1.0000
   2.750   0.6744   0.01075   0.00287  -0.0626   0.4403   1.0000
   3.000   0.7012   0.01097   0.00301  -0.0624   0.4302   1.0000
   3.250   0.7281   0.01119   0.00317  -0.0622   0.4208   1.0000
   3.500   0.7551   0.01140   0.00336  -0.0621   0.4123   1.0000
   3.750   0.7817   0.01165   0.00354  -0.0619   0.4034   1.0000
   4.000   0.8085   0.01186   0.00375  -0.0618   0.3924   1.0000
   4.250   0.8349   0.01211   0.00396  -0.0616   0.3767   1.0000
   4.500   0.8609   0.01238   0.00416  -0.0613   0.3579   1.0000
   4.750   0.8872   0.01262   0.00437  -0.0611   0.3400   1.0000
   5.000   0.9135   0.01287   0.00464  -0.0610   0.3269   1.0000
   5.250   0.9397   0.01313   0.00490  -0.0608   0.3132   1.0000
   5.500   0.9658   0.01340   0.00519  -0.0606   0.2973   1.0000
   5.750   0.9916   0.01371   0.00550  -0.0603   0.2781   1.0000
   6.000   1.0163   0.01415   0.00586  -0.0600   0.2452   1.0000
   6.250   1.0399   0.01475   0.00630  -0.0596   0.2070   1.0000
   6.500   1.0632   0.01541   0.00684  -0.0592   0.1811   1.0000
   6.750   1.0865   0.01605   0.00746  -0.0587   0.1623   1.0000
   7.000   1.1093   0.01677   0.00811  -0.0582   0.1338   1.0000
   7.500   1.1468   0.01927   0.01013  -0.0565   0.0483   1.0000
   7.750   1.1681   0.02011   0.01105  -0.0557   0.0433   1.0000
   8.000   1.1896   0.02086   0.01198  -0.0550   0.0400   1.0000
   8.250   1.2092   0.02182   0.01306  -0.0541   0.0364   1.0000
   8.500   1.2255   0.02310   0.01448  -0.0529   0.0328   1.0000
   8.750   1.2451   0.02392   0.01546  -0.0520   0.0304   1.0000
   9.000   1.2622   0.02494   0.01662  -0.0509   0.0274   1.0000
   9.250   1.2758   0.02625   0.01804  -0.0495   0.0247   1.0000
   9.500   1.2846   0.02792   0.01981  -0.0475   0.0228   1.0000
   9.750   1.2985   0.02902   0.02108  -0.0460   0.0210   1.0000
  10.000   1.3100   0.03023   0.02242  -0.0444   0.0190   1.0000
  10.250   1.3191   0.03140   0.02367  -0.0425   0.0175   1.0000
  10.500   1.3243   0.03294   0.02529  -0.0405   0.0165   1.0000
  10.750   1.3237   0.03515   0.02759  -0.0384   0.0157   1.0000
  11.000   1.3278   0.03713   0.02973  -0.0369   0.0151   1.0000
  11.250   1.3313   0.03926   0.03205  -0.0355   0.0144   1.0000
  11.500   1.3351   0.04145   0.03438  -0.0345   0.0136   1.0000
  11.750   1.3389   0.04367   0.03673  -0.0339   0.0129   1.0000
  12.000   1.3422   0.04603   0.03920  -0.0336   0.0123   1.0000
  12.250   1.3440   0.04864   0.04192  -0.0336   0.0118   1.0000
  12.500   1.3429   0.05173   0.04512  -0.0337   0.0114   1.0000
  12.750   1.3387   0.05529   0.04879  -0.0334   0.0110   1.0000
  13.000   1.3371   0.05869   0.05239  -0.0333   0.0108   1.0000
  13.250   1.3340   0.06234   0.05625  -0.0335   0.0106   1.0000
  13.500   1.3295   0.06628   0.06039  -0.0338   0.0103   1.0000
  13.750   1.3234   0.07054   0.06486  -0.0345   0.0101   1.0000
  14.000   1.3156   0.07514   0.06967  -0.0355   0.0100   1.0000
  14.250   1.3064   0.08010   0.07483  -0.0368   0.0098   1.0000
  14.500   1.2957   0.08545   0.08038  -0.0386   0.0097   1.0000
  14.750   1.2840   0.09119   0.08633  -0.0409   0.0096   1.0000
  15.000   1.2714   0.09736   0.09271  -0.0436   0.0095   1.0000
  15.250   1.2576   0.10395   0.09950  -0.0467   0.0094   1.0000
  15.500   1.2430   0.11097   0.10671  -0.0503   0.0094   1.0000
  15.750   1.2275   0.11850   0.11440  -0.0543   0.0093   1.0000
  16.000   1.2103   0.12675   0.12284  -0.0589   0.0094   1.0000
  16.250   1.1916   0.13579   0.13205  -0.0642   0.0094   1.0000
  16.500   1.1713   0.14587   0.14230  -0.0703   0.0096   1.0000
  16.750   1.1493   0.15728   0.15387  -0.0773   0.0098   1.0000
  17.000   1.1247   0.17070   0.16741  -0.0854   0.0100   1.0000
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