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GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.77 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe336-il-1000000.txt
Download as CSV file: xf-goe336-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 336 (MVA H.44) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3244   0.10485   0.10328  -0.0241   1.0000   0.0155
  -9.250  -0.3218   0.10115   0.09960  -0.0261   1.0000   0.0155
  -9.000  -0.3185   0.09761   0.09606  -0.0279   1.0000   0.0156
  -8.750  -0.3161   0.09405   0.09253  -0.0295   1.0000   0.0156
  -8.500  -0.3128   0.09034   0.08883  -0.0297   0.9986   0.0159
  -8.250  -0.2950   0.08737   0.08586  -0.0330   0.9837   0.0162
  -8.000  -0.2795   0.08432   0.08278  -0.0365   0.9516   0.0165
  -7.750  -0.2752   0.08182   0.08014  -0.0374   0.8982   0.0169
  -7.500  -0.2694   0.07920   0.07731  -0.0392   0.8448   0.0175
  -7.250  -0.2564   0.07425   0.07214  -0.0468   0.7977   0.0194
  -7.000  -0.2420   0.06978   0.06750  -0.0516   0.7699   0.0195
  -6.750  -0.2258   0.06527   0.06286  -0.0557   0.7522   0.0195
  -6.500  -0.2160   0.05949   0.05697  -0.0594   0.7397   0.0200
  -6.250  -0.1982   0.05757   0.05497  -0.0603   0.7279   0.0203
  -5.000  -0.0874   0.03702   0.03372  -0.0722   0.6883   0.0251
  -4.750  -0.0654   0.03572   0.03232  -0.0724   0.6802   0.0255
  -4.500  -0.0420   0.03432   0.03085  -0.0726   0.6718   0.0260
  -4.250  -0.0182   0.03273   0.02914  -0.0729   0.6635   0.0268
  -3.750   0.0276   0.00798   0.00376  -0.0701   0.6354   0.0319
  -3.500   0.0515   0.00742   0.00311  -0.0698   0.6243   0.0324
  -3.000   0.0970   0.01453   0.00910  -0.0696   0.6184   0.0299
  -2.750   0.1226   0.01324   0.00754  -0.0691   0.6066   0.0298
  -2.500   0.1490   0.01234   0.00642  -0.0687   0.5945   0.0297
  -2.250   0.1758   0.01166   0.00557  -0.0683   0.5822   0.0298
  -2.000   0.2027   0.01112   0.00487  -0.0680   0.5703   0.0298
  -1.750   0.2298   0.01080   0.00443  -0.0677   0.5586   0.0301
  -1.500   0.2574   0.01062   0.00416  -0.0675   0.5480   0.0305
  -1.250   0.2847   0.01034   0.00380  -0.0673   0.5385   0.0307
  -1.000   0.3108   0.00967   0.00301  -0.0669   0.5295   0.0313
  -0.750   0.3376   0.00931   0.00259  -0.0665   0.5210   0.0320
  -0.500   0.3643   0.00913   0.00234  -0.0662   0.5124   0.0325
  -0.250   0.3915   0.00897   0.00215  -0.0660   0.5047   0.0331
   0.000   0.4185   0.00889   0.00201  -0.0658   0.4975   0.0337
   0.250   0.4460   0.00878   0.00189  -0.0656   0.4914   0.0344
   0.500   0.4731   0.00873   0.00180  -0.0654   0.4842   0.0353
   0.750   0.5005   0.00868   0.00172  -0.0652   0.4778   0.0368
   1.000   0.5279   0.00865   0.00166  -0.0651   0.4718   0.0381
   1.250   0.5552   0.00864   0.00161  -0.0649   0.4659   0.0409
   1.500   0.5825   0.00856   0.00161  -0.0647   0.4592   0.0591
   1.750   0.6095   0.00857   0.00167  -0.0646   0.4527   0.0902
   2.000   0.6373   0.00858   0.00170  -0.0645   0.4472   0.1002
   2.250   0.6648   0.00859   0.00173  -0.0645   0.4422   0.1113
   2.500   0.6919   0.00864   0.00179  -0.0643   0.4370   0.1234
   2.750   0.7194   0.00859   0.00183  -0.0643   0.4325   0.1514
   3.000   0.7452   0.00840   0.00195  -0.0640   0.4266   0.3060
   3.250   0.8127   0.00721   0.00231  -0.0734   0.4186   0.9947
   3.500   0.8717   0.00733   0.00238  -0.0805   0.4107   1.0000
   3.750   0.8974   0.00743   0.00244  -0.0801   0.4049   1.0000
   4.000   0.9233   0.00750   0.00251  -0.0798   0.3985   1.0000
   4.250   0.9487   0.00762   0.00259  -0.0793   0.3903   1.0000
   4.500   0.9738   0.00777   0.00267  -0.0788   0.3768   1.0000
   4.750   0.9986   0.00794   0.00277  -0.0783   0.3558   1.0000
   5.000   1.0214   0.00830   0.00294  -0.0775   0.3171   1.0000
   5.250   1.0378   0.00932   0.00348  -0.0757   0.2319   1.0000
   5.500   1.0590   0.00981   0.00381  -0.0746   0.2038   1.0000
   5.750   1.0799   0.01029   0.00414  -0.0735   0.1732   1.0000
   6.000   1.0980   0.01102   0.00458  -0.0720   0.1260   1.0000
   6.250   1.1184   0.01149   0.00494  -0.0708   0.1068   1.0000
   6.500   1.1391   0.01192   0.00527  -0.0696   0.0879   1.0000
   6.750   1.1563   0.01261   0.00578  -0.0679   0.0579   1.0000
   7.000   1.1769   0.01299   0.00614  -0.0667   0.0525   1.0000
   7.250   1.1984   0.01329   0.00644  -0.0656   0.0479   1.0000
   7.500   1.2193   0.01362   0.00675  -0.0645   0.0428   1.0000
   7.750   1.2357   0.01426   0.00724  -0.0626   0.0223   1.0000
   8.000   1.2528   0.01482   0.00781  -0.0608   0.0152   1.0000
   8.250   1.2711   0.01529   0.00832  -0.0592   0.0136   1.0000
   8.500   1.2892   0.01574   0.00882  -0.0576   0.0125   1.0000
   8.750   1.3072   0.01616   0.00929  -0.0560   0.0121   1.0000
   9.000   1.3239   0.01664   0.00983  -0.0543   0.0116   1.0000
   9.250   1.3392   0.01719   0.01042  -0.0523   0.0111   1.0000
   9.500   1.3528   0.01781   0.01109  -0.0500   0.0106   1.0000
   9.750   1.3635   0.01854   0.01189  -0.0473   0.0102   1.0000
  10.000   1.3664   0.01947   0.01290  -0.0433   0.0098   1.0000
  10.250   1.3727   0.02037   0.01387  -0.0402   0.0095   1.0000
  10.500   1.3848   0.02105   0.01461  -0.0382   0.0092   1.0000
  10.750   1.3950   0.02190   0.01552  -0.0361   0.0089   1.0000
  11.000   1.4035   0.02295   0.01663  -0.0340   0.0087   1.0000
  11.250   1.4109   0.02416   0.01791  -0.0321   0.0084   1.0000
  11.500   1.4175   0.02553   0.01936  -0.0303   0.0082   1.0000
  11.750   1.4231   0.02711   0.02100  -0.0288   0.0080   1.0000
  12.000   1.4275   0.02892   0.02290  -0.0276   0.0078   1.0000
  12.250   1.4304   0.03103   0.02508  -0.0266   0.0076   1.0000
  12.500   1.4309   0.03349   0.02764  -0.0257   0.0075   1.0000
  12.750   1.4279   0.03644   0.03067  -0.0251   0.0073   1.0000
  13.000   1.4208   0.03987   0.03420  -0.0245   0.0072   1.0000
  13.250   1.4102   0.04373   0.03815  -0.0239   0.0071   1.0000
  13.500   1.3990   0.04765   0.04217  -0.0233   0.0070   1.0000
  13.750   1.4019   0.05019   0.04478  -0.0232   0.0069   1.0000
  14.000   1.4036   0.05288   0.04756  -0.0232   0.0069   1.0000
  14.250   1.4030   0.05587   0.05063  -0.0232   0.0068   1.0000
  14.500   1.4020   0.05899   0.05383  -0.0233   0.0067   1.0000
  14.750   1.4012   0.06214   0.05707  -0.0235   0.0066   1.0000
  15.000   1.4001   0.06538   0.06039  -0.0237   0.0065   1.0000
  15.250   1.3988   0.06870   0.06379  -0.0241   0.0064   1.0000
  15.500   1.3971   0.07213   0.06729  -0.0246   0.0063   1.0000
  15.750   1.3951   0.07563   0.07088  -0.0251   0.0061   1.0000
  16.000   1.3927   0.07922   0.07454  -0.0257   0.0060   1.0000
  16.250   1.3897   0.08292   0.07832  -0.0263   0.0059   1.0000
  16.500   1.3867   0.08666   0.08213  -0.0270   0.0058   1.0000
  16.750   1.3838   0.09039   0.08593  -0.0277   0.0057   1.0000
  17.000   1.3802   0.09426   0.08988  -0.0286   0.0057   1.0000
  17.250   1.3767   0.09818   0.09388  -0.0295   0.0056   1.0000
  17.500   1.3734   0.10210   0.09787  -0.0305   0.0055   1.0000
  17.750   1.3696   0.10614   0.10198  -0.0316   0.0055   1.0000
  18.000   1.3660   0.11019   0.10611  -0.0329   0.0054   1.0000
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