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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 500,000
Max Cl/Cd: 99.04 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe142-il-500000.txt
Download as CSV file: xf-goe142-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3941   0.09667   0.09445  -0.0084   1.0000   0.0141
  -7.750  -0.3873   0.09349   0.09130  -0.0110   1.0000   0.0150
  -7.500  -0.3830   0.09066   0.08851  -0.0146   1.0000   0.0153
  -6.500  -0.3454   0.07473   0.07265  -0.0297   1.0000   0.0158
  -6.250  -0.3435   0.07151   0.06945  -0.0289   1.0000   0.0162
  -6.000  -0.3395   0.06933   0.06729  -0.0278   1.0000   0.0165
  -5.750  -0.3361   0.06732   0.06530  -0.0269   1.0000   0.0170
  -5.500  -0.3090   0.06361   0.06154  -0.0322   0.9979   0.0181
  -5.250  -0.2697   0.05862   0.05648  -0.0408   0.9950   0.0194
  -5.000  -0.2166   0.05327   0.05096  -0.0517   0.9911   0.0216
  -4.750  -0.1734   0.04853   0.04608  -0.0585   0.9877   0.0218
  -4.500  -0.1315   0.04335   0.04073  -0.0648   0.9851   0.0219
  -4.250  -0.1007   0.03676   0.03400  -0.0707   0.9817   0.0235
  -4.000  -0.0666   0.03425   0.03139  -0.0738   0.9772   0.0250
  -3.750  -0.0225   0.03157   0.02844  -0.0770   0.9732   0.0301
  -3.500   0.0161   0.02850   0.02506  -0.0793   0.9680   0.0307
  -3.250   0.0493   0.01663   0.01211  -0.0819   0.9607   0.0222
  -3.000   0.0803   0.01312   0.00801  -0.0826   0.9536   0.0228
  -2.750   0.1083   0.01186   0.00655  -0.0824   0.9438   0.0241
  -2.500   0.1351   0.01159   0.00623  -0.0819   0.9324   0.0265
  -2.250   0.1618   0.01085   0.00532  -0.0812   0.9207   0.0286
  -2.000   0.1883   0.01035   0.00468  -0.0805   0.9080   0.0304
  -1.750   0.2142   0.00928   0.00347  -0.0798   0.8947   0.0341
  -1.500   0.2406   0.00914   0.00328  -0.0791   0.8798   0.0387
  -1.250   0.2672   0.00902   0.00307  -0.0785   0.8637   0.0419
  -1.000   0.2935   0.00848   0.00247  -0.0780   0.8468   0.0490
  -0.750   0.3203   0.00843   0.00231  -0.0774   0.8287   0.0544
  -0.500   0.3472   0.00813   0.00197  -0.0770   0.8089   0.0633
  -0.250   0.3741   0.00801   0.00178  -0.0766   0.7883   0.0735
   0.000   0.4012   0.00793   0.00163  -0.0762   0.7662   0.0861
   0.250   0.4282   0.00787   0.00153  -0.0759   0.7436   0.1048
   0.500   0.4553   0.00780   0.00146  -0.0756   0.7195   0.1379
   0.750   0.4767   0.00613   0.00157  -0.0750   0.6967   0.8041
   1.000   0.5047   0.00592   0.00148  -0.0745   0.6714   1.0000
   1.250   0.5316   0.00608   0.00147  -0.0741   0.6457   1.0000
   1.500   0.5586   0.00626   0.00149  -0.0739   0.6194   1.0000
   1.750   0.5856   0.00644   0.00152  -0.0736   0.5931   1.0000
   2.000   0.6125   0.00664   0.00157  -0.0733   0.5672   1.0000
   2.250   0.6393   0.00684   0.00163  -0.0731   0.5416   1.0000
   2.500   0.6661   0.00706   0.00171  -0.0729   0.5164   1.0000
   2.750   0.6931   0.00726   0.00181  -0.0727   0.4926   1.0000
   3.000   0.7199   0.00748   0.00192  -0.0725   0.4695   1.0000
   3.250   0.7467   0.00771   0.00204  -0.0723   0.4468   1.0000
   3.500   0.7735   0.00793   0.00217  -0.0721   0.4262   1.0000
   3.750   0.8002   0.00817   0.00233  -0.0719   0.4055   1.0000
   4.000   0.8269   0.00841   0.00249  -0.0717   0.3857   1.0000
   4.250   0.8536   0.00864   0.00266  -0.0716   0.3673   1.0000
   4.500   0.8801   0.00890   0.00285  -0.0714   0.3493   1.0000
   4.750   0.9065   0.00917   0.00307  -0.0712   0.3320   1.0000
   5.000   0.9330   0.00942   0.00329  -0.0710   0.3160   1.0000
   5.250   0.9593   0.00969   0.00351  -0.0708   0.3000   1.0000
   5.500   0.9856   0.00996   0.00376  -0.0705   0.2850   1.0000
   5.750   1.0116   0.01026   0.00403  -0.0703   0.2679   1.0000
   6.000   1.0372   0.01061   0.00429  -0.0700   0.2478   1.0000
   6.250   1.0630   0.01091   0.00456  -0.0698   0.2306   1.0000
   6.500   1.0887   0.01124   0.00486  -0.0695   0.2142   1.0000
   6.750   1.1141   0.01160   0.00519  -0.0693   0.1974   1.0000
   7.000   1.1392   0.01198   0.00553  -0.0689   0.1807   1.0000
   7.250   1.1643   0.01237   0.00590  -0.0686   0.1634   1.0000
   7.500   1.1885   0.01287   0.00631  -0.0682   0.1404   1.0000
   7.750   1.2117   0.01351   0.00682  -0.0677   0.1099   1.0000
   8.000   1.2304   0.01481   0.00776  -0.0667   0.0547   1.0000
   8.250   1.2496   0.01605   0.00885  -0.0656   0.0303   1.0000
   8.500   1.2705   0.01701   0.00984  -0.0646   0.0235   1.0000
   8.750   1.2915   0.01789   0.01084  -0.0637   0.0205   1.0000
   9.000   1.3124   0.01873   0.01177  -0.0627   0.0182   1.0000
   9.250   1.3292   0.02004   0.01318  -0.0613   0.0161   1.0000
   9.500   1.3434   0.02160   0.01493  -0.0594   0.0148   1.0000
   9.750   1.3629   0.02240   0.01583  -0.0583   0.0138   1.0000
  10.000   1.3794   0.02352   0.01706  -0.0569   0.0129   1.0000
  10.250   1.3942   0.02472   0.01837  -0.0553   0.0122   1.0000
  10.500   1.4075   0.02601   0.01976  -0.0535   0.0116   1.0000
  10.750   1.4173   0.02754   0.02141  -0.0514   0.0110   1.0000
  11.000   1.4191   0.02975   0.02375  -0.0484   0.0105   1.0000
  11.250   1.4098   0.03304   0.02725  -0.0440   0.0100   1.0000
  11.500   1.4197   0.03395   0.02829  -0.0422   0.0098   1.0000
  11.750   1.4258   0.03539   0.02990  -0.0402   0.0094   1.0000
  12.000   1.4282   0.03735   0.03202  -0.0382   0.0091   1.0000
  12.250   1.4281   0.03972   0.03455  -0.0364   0.0089   1.0000
  12.500   1.4268   0.04233   0.03733  -0.0351   0.0086   1.0000
  12.750   1.4241   0.04526   0.04042  -0.0341   0.0084   1.0000
  13.000   1.4198   0.04854   0.04388  -0.0335   0.0083   1.0000
  13.250   1.4145   0.05212   0.04763  -0.0335   0.0081   1.0000
  13.500   1.4075   0.05614   0.05182  -0.0340   0.0080   1.0000
  13.750   1.3989   0.06060   0.05645  -0.0351   0.0079   1.0000
  14.000   1.3888   0.06551   0.06154  -0.0366   0.0078   1.0000
  14.250   1.3767   0.07098   0.06718  -0.0386   0.0077   1.0000
  14.500   1.3627   0.07695   0.07333  -0.0411   0.0077   1.0000
  14.750   1.3482   0.08327   0.07981  -0.0440   0.0077   1.0000
  15.000   1.3317   0.09020   0.08691  -0.0474   0.0077   1.0000
  15.250   1.3137   0.09773   0.09461  -0.0512   0.0077   1.0000
  15.500   1.2961   0.10553   0.10257  -0.0554   0.0077   1.0000
  15.750   1.2752   0.11431   0.11153  -0.0602   0.0078   1.0000
  16.000   1.2524   0.12406   0.12145  -0.0657   0.0079   1.0000
  16.250   1.2275   0.13488   0.13244  -0.0720   0.0081   1.0000
  16.500   1.2011   0.14673   0.14445  -0.0790   0.0083   1.0000
  16.750   1.1744   0.15958   0.15744  -0.0867   0.0086   1.0000
  17.000   1.1416   0.17582   0.17379  -0.0963   0.0091   1.0000
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