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GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il)
Reynolds number: 200,000
Max Cl/Cd: 77.18 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe326-il-200000.txt
Download as CSV file: xf-goe326-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 326 (PFALZ 55) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3258   0.08940   0.08615  -0.0263   1.0000   0.0383
  -7.250  -0.3237   0.08752   0.08434  -0.0334   1.0000   0.0391
  -7.000  -0.3251   0.08558   0.08245  -0.0359   1.0000   0.0393
  -6.750  -0.3334   0.08408   0.08099  -0.0350   1.0000   0.0394
  -6.250  -0.3094   0.07389   0.07083  -0.0379   0.9944   0.0405
  -6.000  -0.2845   0.06990   0.06683  -0.0405   0.9891   0.0418
  -5.750  -0.2505   0.06551   0.06237  -0.0471   0.9841   0.0439
  -5.500  -0.1835   0.06061   0.05704  -0.0651   0.9751   0.0500
  -5.250  -0.1541   0.05351   0.04987  -0.0709   0.9713   0.0512
  -5.000  -0.1300   0.05011   0.04651  -0.0726   0.9649   0.0526
  -4.750  -0.0961   0.04679   0.04311  -0.0766   0.9596   0.0555
  -4.500  -0.0433   0.04260   0.03824  -0.0850   0.9524   0.0635
  -4.250  -0.0185   0.03872   0.03450  -0.0869   0.9457   0.0655
  -4.000   0.0111   0.03632   0.03203  -0.0887   0.9381   0.0689
  -3.750   0.0501   0.03347   0.02859  -0.0918   0.9298   0.0782
  -3.500   0.0729   0.03114   0.02637  -0.0922   0.9201   0.0815
  -3.250   0.1048   0.02936   0.02414  -0.0932   0.9117   0.0932
  -3.000   0.1274   0.02744   0.02227  -0.0930   0.9008   0.0970
  -2.750   0.1540   0.02598   0.02050  -0.0929   0.8901   0.1095
  -2.500   0.1797   0.02485   0.01916  -0.0926   0.8799   0.1238
  -2.250   0.2035   0.02357   0.01781  -0.0921   0.8692   0.1397
  -1.500   0.2926   0.01816   0.01115  -0.0895   0.8372   0.0879
  -1.250   0.3216   0.01743   0.00996  -0.0883   0.8252   0.0772
  -1.000   0.3484   0.01661   0.00899  -0.0876   0.8127   0.0770
  -0.750   0.3751   0.01535   0.00760  -0.0869   0.8004   0.0754
  -0.500   0.4019   0.01459   0.00671  -0.0862   0.7874   0.0749
  -0.250   0.4287   0.01402   0.00603  -0.0854   0.7740   0.0753
   0.000   0.4553   0.01358   0.00551  -0.0847   0.7596   0.0763
   0.250   0.4815   0.01299   0.00489  -0.0841   0.7448   0.0794
   0.500   0.5077   0.01266   0.00456  -0.0835   0.7291   0.0843
   0.750   0.5343   0.01242   0.00428  -0.0829   0.7129   0.0884
   1.000   0.5609   0.01220   0.00400  -0.0824   0.6963   0.0949
   1.250   0.5878   0.01203   0.00381  -0.0820   0.6794   0.1111
   1.500   0.6155   0.00994   0.00371  -0.0818   0.6630   1.0000
   1.750   0.6422   0.01006   0.00363  -0.0812   0.6460   1.0000
   2.000   0.6688   0.01019   0.00359  -0.0808   0.6293   1.0000
   2.250   0.6954   0.01032   0.00361  -0.0804   0.6117   1.0000
   2.500   0.7218   0.01048   0.00364  -0.0800   0.5942   1.0000
   2.750   0.7480   0.01067   0.00369  -0.0795   0.5772   1.0000
   3.000   0.7742   0.01091   0.00380  -0.0791   0.5613   1.0000
   3.250   0.8003   0.01117   0.00394  -0.0787   0.5461   1.0000
   3.500   0.8264   0.01146   0.00412  -0.0784   0.5313   1.0000
   3.750   0.8524   0.01175   0.00434  -0.0780   0.5166   1.0000
   4.000   0.8785   0.01204   0.00456  -0.0776   0.5028   1.0000
   4.250   0.9045   0.01234   0.00481  -0.0773   0.4902   1.0000
   4.500   0.9306   0.01265   0.00506  -0.0770   0.4786   1.0000
   4.750   0.9566   0.01294   0.00533  -0.0767   0.4668   1.0000
   5.000   0.9824   0.01318   0.00559  -0.0763   0.4540   1.0000
   5.250   1.0082   0.01344   0.00587  -0.0760   0.4419   1.0000
   5.500   1.0339   0.01371   0.00616  -0.0756   0.4303   1.0000
   5.750   1.0593   0.01398   0.00643  -0.0752   0.4186   1.0000
   6.000   1.0844   0.01425   0.00669  -0.0748   0.4064   1.0000
   6.250   1.1095   0.01450   0.00699  -0.0743   0.3939   1.0000
   6.500   1.1340   0.01476   0.00729  -0.0738   0.3794   1.0000
   6.750   1.1579   0.01504   0.00756  -0.0732   0.3631   1.0000
   7.000   1.1816   0.01531   0.00788  -0.0726   0.3445   1.0000
   7.250   1.2046   0.01563   0.00821  -0.0719   0.3236   1.0000
   7.500   1.2271   0.01603   0.00861  -0.0711   0.3032   1.0000
   7.750   1.2491   0.01647   0.00905  -0.0703   0.2777   1.0000
   8.000   1.2697   0.01704   0.00955  -0.0694   0.2470   1.0000
   8.250   1.2892   0.01776   0.01015  -0.0683   0.2093   1.0000
   8.500   1.3059   0.01874   0.01094  -0.0670   0.1677   1.0000
   8.750   1.3218   0.01982   0.01183  -0.0656   0.1404   1.0000
   9.000   1.3371   0.02090   0.01282  -0.0642   0.1218   1.0000
   9.250   1.3535   0.02186   0.01377  -0.0628   0.1044   1.0000
   9.500   1.3693   0.02284   0.01470  -0.0613   0.0804   1.0000
   9.750   1.3770   0.02446   0.01601  -0.0589   0.0434   1.0000
  10.000   1.3833   0.02604   0.01753  -0.0562   0.0339   1.0000
  10.250   1.3889   0.02739   0.01897  -0.0533   0.0305   1.0000
  10.500   1.3942   0.02881   0.02051  -0.0507   0.0286   1.0000
  10.750   1.3971   0.03048   0.02230  -0.0482   0.0273   1.0000
  11.000   1.3970   0.03252   0.02447  -0.0459   0.0263   1.0000
  11.250   1.3936   0.03497   0.02706  -0.0437   0.0255   1.0000
  11.500   1.3917   0.03748   0.02970  -0.0421   0.0251   1.0000
  11.750   1.3913   0.04001   0.03237  -0.0408   0.0247   1.0000
  12.000   1.3903   0.04271   0.03523  -0.0397   0.0244   1.0000
  12.250   1.3894   0.04551   0.03816  -0.0388   0.0240   1.0000
  12.500   1.3885   0.04837   0.04115  -0.0381   0.0235   1.0000
  12.750   1.3878   0.05127   0.04417  -0.0374   0.0229   1.0000
  13.000   1.3869   0.05424   0.04724  -0.0368   0.0223   1.0000
  13.250   1.3863   0.05721   0.05031  -0.0363   0.0218   1.0000
  13.500   1.3865   0.06013   0.05332  -0.0356   0.0214   1.0000
  13.750   1.3876   0.06296   0.05626  -0.0348   0.0212   1.0000
  14.000   1.3895   0.06576   0.05916  -0.0340   0.0209   1.0000
  14.250   1.3916   0.06861   0.06213  -0.0331   0.0207   1.0000
  14.500   1.3926   0.07170   0.06538  -0.0325   0.0206   1.0000
  14.750   1.3921   0.07509   0.06894  -0.0321   0.0205   1.0000
  15.000   1.3890   0.07891   0.07296  -0.0322   0.0205   1.0000
  15.250   1.3834   0.08318   0.07744  -0.0327   0.0206   1.0000
  15.500   1.3752   0.08797   0.08246  -0.0338   0.0207   1.0000
  15.750   1.3644   0.09332   0.08806  -0.0355   0.0208   1.0000
  16.000   1.3511   0.09926   0.09425  -0.0378   0.0210   1.0000
  16.250   1.3358   0.10581   0.10106  -0.0407   0.0212   1.0000
  16.500   1.3178   0.11316   0.10866  -0.0444   0.0214   1.0000
  16.750   1.2968   0.12153   0.11729  -0.0492   0.0217   1.0000
  17.000   1.2743   0.13065   0.12666  -0.0548   0.0220   1.0000
  17.250   1.2505   0.14071   0.13694  -0.0613   0.0223   1.0000
  17.500   1.2243   0.15217   0.14861  -0.0691   0.0227   1.0000
  17.750   1.1929   0.16617   0.16279  -0.0787   0.0232   1.0000
  18.000   1.1449   0.18796   0.18470  -0.0928   0.0243   1.0000
  18.250   1.1305   0.19864   0.19535  -0.0985   0.0253   1.0000
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