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GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.07 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe310-il-1000000.txt
Download as CSV file: xf-goe310-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 310 (MVA H.42) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3550   0.10695   0.10529  -0.0323   1.0000   0.0126
 -10.000  -0.3534   0.10367   0.10203  -0.0328   1.0000   0.0126
  -9.750  -0.3570   0.09962   0.09800  -0.0330   1.0000   0.0129
  -9.500  -0.3539   0.09727   0.09567  -0.0328   1.0000   0.0130
  -9.250  -0.3512   0.09517   0.09359  -0.0323   1.0000   0.0132
  -9.000  -0.3501   0.09319   0.09163  -0.0317   1.0000   0.0134
  -8.750  -0.3488   0.09067   0.08913  -0.0320   0.9997   0.0135
  -8.500  -0.3341   0.08694   0.08540  -0.0362   0.9983   0.0139
  -8.250  -0.3187   0.08305   0.08151  -0.0411   0.9953   0.0150
  -8.000  -0.3097   0.07589   0.07436  -0.0512   0.9870   0.0162
  -7.000  -0.2683   0.02634   0.02376  -0.0946   0.9484   0.0146
  -6.750  -0.2550   0.02150   0.01826  -0.0942   0.9386   0.0158
  -6.500  -0.2399   0.01880   0.01505  -0.0926   0.9292   0.0167
  -6.250  -0.2170   0.01805   0.01423  -0.0921   0.9221   0.0172
  -6.000  -0.1917   0.01777   0.01393  -0.0918   0.9148   0.0177
  -5.750  -0.1686   0.01709   0.01312  -0.0910   0.9073   0.0184
  -5.500  -0.1460   0.01626   0.01209  -0.0900   0.8991   0.0193
  -5.250  -0.1232   0.01552   0.01113  -0.0889   0.8909   0.0202
  -5.000  -0.1008   0.01481   0.01011  -0.0877   0.8825   0.0216
  -4.750  -0.0784   0.01372   0.00899  -0.0868   0.8738   0.0225
  -4.500  -0.0541   0.01314   0.00835  -0.0862   0.8648   0.0233
  -4.250  -0.0301   0.01253   0.00763  -0.0853   0.8538   0.0241
  -4.000  -0.0058   0.01193   0.00690  -0.0844   0.8417   0.0247
  -3.750   0.0192   0.01166   0.00651  -0.0836   0.8277   0.0259
  -3.500   0.0444   0.01189   0.00655  -0.0828   0.8109   0.0275
  -3.250   0.0682   0.01115   0.00566  -0.0818   0.7912   0.0276
  -3.000   0.0920   0.01058   0.00495  -0.0808   0.7682   0.0276
  -2.750   0.1150   0.00990   0.00414  -0.0797   0.7456   0.0279
  -2.500   0.1379   0.00929   0.00345  -0.0786   0.7249   0.0288
  -2.250   0.1616   0.00900   0.00307  -0.0776   0.7062   0.0296
  -2.000   0.1859   0.00878   0.00276  -0.0767   0.6897   0.0301
  -1.750   0.2105   0.00860   0.00250  -0.0759   0.6749   0.0304
  -1.500   0.2355   0.00844   0.00228  -0.0752   0.6618   0.0307
  -1.250   0.2606   0.00830   0.00208  -0.0745   0.6500   0.0311
  -1.000   0.2858   0.00819   0.00190  -0.0739   0.6390   0.0314
  -0.750   0.3111   0.00810   0.00175  -0.0732   0.6288   0.0322
  -0.500   0.3362   0.00802   0.00161  -0.0726   0.6158   0.0328
  -0.250   0.3611   0.00798   0.00149  -0.0718   0.6013   0.0335
   0.000   0.3866   0.00793   0.00139  -0.0712   0.5907   0.0344
   0.250   0.4119   0.00792   0.00133  -0.0706   0.5816   0.0348
   0.500   0.4379   0.00789   0.00126  -0.0701   0.5725   0.0359
   0.750   0.4633   0.00790   0.00122  -0.0696   0.5616   0.0374
   1.000   0.4884   0.00793   0.00119  -0.0689   0.5472   0.0402
   1.250   0.5113   0.00775   0.00118  -0.0679   0.5337   0.1150
   1.750   0.5607   0.00775   0.00132  -0.0666   0.5092   0.1921
   2.000   0.5858   0.00780   0.00137  -0.0660   0.4951   0.2047
   2.250   0.6106   0.00788   0.00141  -0.0653   0.4787   0.2132
   2.500   0.6353   0.00798   0.00146  -0.0647   0.4612   0.2211
   2.750   0.6589   0.00811   0.00153  -0.0639   0.4345   0.2306
   3.000   0.6804   0.00837   0.00164  -0.0627   0.3901   0.2424
   3.250   0.6973   0.00892   0.00189  -0.0607   0.3127   0.2650
   3.500   0.7116   0.00946   0.00229  -0.0583   0.2319   0.3671
   3.750   0.7184   0.00923   0.00256  -0.0543   0.1803   0.7032
   4.250   0.8599   0.01041   0.00382  -0.0747   0.0568   0.9948
   4.500   0.9096   0.01064   0.00404  -0.0798   0.0555   0.9985
   4.750   0.9455   0.01086   0.00428  -0.0818   0.0545   1.0000
   5.000   0.9665   0.01110   0.00453  -0.0805   0.0532   1.0000
   5.250   0.9870   0.01137   0.00481  -0.0790   0.0515   1.0000
   5.500   1.0067   0.01168   0.00514  -0.0775   0.0491   1.0000
   5.750   1.0257   0.01203   0.00554  -0.0758   0.0471   1.0000
   6.000   1.0467   0.01224   0.00576  -0.0745   0.0466   1.0000
   6.250   1.0672   0.01247   0.00602  -0.0731   0.0459   1.0000
   6.500   1.0878   0.01268   0.00625  -0.0718   0.0445   1.0000
   6.750   1.1077   0.01294   0.00652  -0.0703   0.0430   1.0000
   7.000   1.1272   0.01321   0.00681  -0.0687   0.0414   1.0000
   7.250   1.1459   0.01352   0.00714  -0.0671   0.0396   1.0000
   7.500   1.1615   0.01401   0.00767  -0.0649   0.0368   1.0000
   7.750   1.1862   0.01394   0.00758  -0.0643   0.0352   1.0000
   8.000   1.2086   0.01399   0.00759  -0.0634   0.0304   1.0000
   8.250   1.2268   0.01429   0.00778  -0.0617   0.0216   1.0000
   8.500   1.2415   0.01478   0.00822  -0.0593   0.0169   1.0000
   8.750   1.2567   0.01523   0.00872  -0.0571   0.0154   1.0000
   9.000   1.2706   0.01574   0.00926  -0.0546   0.0142   1.0000
   9.250   1.2813   0.01633   0.00988  -0.0515   0.0128   1.0000
   9.500   1.2880   0.01691   0.01052  -0.0477   0.0121   1.0000
   9.750   1.2985   0.01736   0.01104  -0.0446   0.0117   1.0000
  10.000   1.3084   0.01791   0.01164  -0.0416   0.0112   1.0000
  10.250   1.3184   0.01851   0.01231  -0.0387   0.0108   1.0000
  10.500   1.3274   0.01923   0.01307  -0.0359   0.0102   1.0000
  10.750   1.3354   0.02005   0.01396  -0.0331   0.0098   1.0000
  11.000   1.3402   0.02111   0.01509  -0.0300   0.0095   1.0000
  11.250   1.3334   0.02297   0.01710  -0.0257   0.0090   1.0000
  11.500   1.3443   0.02380   0.01800  -0.0238   0.0089   1.0000
  11.750   1.3521   0.02490   0.01918  -0.0218   0.0087   1.0000
  12.000   1.3592   0.02610   0.02046  -0.0198   0.0085   1.0000
  12.250   1.3670   0.02731   0.02174  -0.0181   0.0082   1.0000
  12.500   1.3757   0.02849   0.02298  -0.0166   0.0079   1.0000
  12.750   1.3791   0.03018   0.02476  -0.0149   0.0077   1.0000
  13.000   1.3850   0.03173   0.02638  -0.0135   0.0074   1.0000
  13.250   1.3858   0.03381   0.02857  -0.0121   0.0074   1.0000
  13.500   1.3907   0.03562   0.03044  -0.0111   0.0071   1.0000
  13.750   1.3931   0.03774   0.03263  -0.0102   0.0069   1.0000
  14.000   1.3906   0.04043   0.03543  -0.0093   0.0069   1.0000
  14.250   1.3834   0.04371   0.03881  -0.0085   0.0066   1.0000
  14.500   1.3676   0.04801   0.04327  -0.0074   0.0064   1.0000
  14.750   1.3599   0.05156   0.04695  -0.0068   0.0064   1.0000
  15.000   1.3636   0.05399   0.04948  -0.0070   0.0063   1.0000
  15.250   1.3613   0.05715   0.05275  -0.0069   0.0063   1.0000
  15.500   1.3649   0.05976   0.05545  -0.0074   0.0061   1.0000
  15.750   1.3587   0.06351   0.05932  -0.0075   0.0061   1.0000
  16.000   1.3553   0.06708   0.06301  -0.0080   0.0060   1.0000
  16.250   1.3529   0.07061   0.06665  -0.0088   0.0059   1.0000
  16.500   1.3449   0.07491   0.07108  -0.0095   0.0060   1.0000
  16.750   1.3396   0.07904   0.07532  -0.0106   0.0058   1.0000
  17.000   1.3288   0.08398   0.08040  -0.0118   0.0059   1.0000
  17.250   1.3237   0.08836   0.08489  -0.0133   0.0057   1.0000
  17.500   1.3127   0.09364   0.09030  -0.0150   0.0057   1.0000
  17.750   1.2983   0.09960   0.09640  -0.0170   0.0057   1.0000
  18.000   1.2910   0.10466   0.10157  -0.0191   0.0056   1.0000
  18.250   1.2762   0.11109   0.10815  -0.0217   0.0056   1.0000
  18.500   1.2639   0.11721   0.11439  -0.0245   0.0056   1.0000
  18.750   1.2502   0.12383   0.12113  -0.0276   0.0055   1.0000
  19.000   1.2310   0.13169   0.12915  -0.0314   0.0056   1.0000
  19.250   1.2267   0.13683   0.13436  -0.0341   0.0054   1.0000
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