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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.16 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe325-il-1000000-n5.txt
Download as CSV file: xf-goe325-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 325 (PFALZ 54) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3648   0.10013   0.09858  -0.0205   1.0000   0.0049
  -9.000  -0.3593   0.09566   0.09411  -0.0235   0.9927   0.0051
  -7.500  -0.3571   0.01379   0.00980  -0.0917   0.9356   0.0108
  -7.250  -0.3306   0.01292   0.00878  -0.0916   0.9308   0.0119
  -7.000  -0.3032   0.01293   0.00881  -0.0914   0.9257   0.0131
  -6.750  -0.2761   0.01273   0.00857  -0.0912   0.9204   0.0142
  -6.500  -0.2495   0.01198   0.00764  -0.0910   0.9121   0.0153
  -6.250  -0.2222   0.01218   0.00787  -0.0907   0.9003   0.0159
  -6.000  -0.1949   0.01263   0.00836  -0.0902   0.8844   0.0165
  -5.750  -0.1682   0.01297   0.00867  -0.0897   0.8583   0.0171
  -5.500  -0.1423   0.01307   0.00858  -0.0891   0.8143   0.0177
  -5.250  -0.1162   0.01306   0.00830  -0.0886   0.7640   0.0186
  -5.000  -0.0891   0.01290   0.00792  -0.0885   0.7295   0.0195
  -4.750  -0.0617   0.01276   0.00759  -0.0884   0.7013   0.0202
  -4.500  -0.0342   0.01273   0.00739  -0.0883   0.6680   0.0206
  -4.250  -0.0069   0.01284   0.00728  -0.0882   0.6209   0.0209
  -4.000   0.0199   0.01190   0.00597  -0.0883   0.5762   0.0218
  -3.750   0.0475   0.01161   0.00551  -0.0883   0.5498   0.0226
  -3.500   0.0754   0.01142   0.00520  -0.0884   0.5317   0.0231
  -3.250   0.1034   0.01126   0.00494  -0.0884   0.5191   0.0237
  -3.000   0.1316   0.01109   0.00470  -0.0885   0.5100   0.0243
  -2.750   0.1598   0.01080   0.00431  -0.0885   0.5014   0.0248
  -2.500   0.1880   0.01051   0.00394  -0.0886   0.4931   0.0252
  -2.250   0.2162   0.01023   0.00356  -0.0886   0.4843   0.0255
  -2.000   0.2445   0.00997   0.00323  -0.0887   0.4771   0.0258
  -1.750   0.2727   0.00973   0.00292  -0.0888   0.4691   0.0261
  -1.500   0.3010   0.00951   0.00264  -0.0888   0.4609   0.0263
  -1.250   0.3293   0.00936   0.00241  -0.0889   0.4514   0.0266
  -1.000   0.3576   0.00923   0.00223  -0.0890   0.4413   0.0271
  -0.750   0.3859   0.00910   0.00203  -0.0890   0.4318   0.0273
  -0.500   0.4142   0.00900   0.00186  -0.0891   0.4207   0.0275
  -0.250   0.4424   0.00895   0.00173  -0.0891   0.4073   0.0279
   0.000   0.4705   0.00894   0.00164  -0.0892   0.3920   0.0285
   0.250   0.4985   0.00897   0.00160  -0.0892   0.3772   0.0291
   0.500   0.5265   0.00901   0.00158  -0.0893   0.3645   0.0295
   0.750   0.5546   0.00903   0.00155  -0.0893   0.3539   0.0302
   1.000   0.5827   0.00904   0.00151  -0.0894   0.3449   0.0319
   1.500   0.6387   0.00914   0.00152  -0.0895   0.3287   0.0353
   2.000   0.6946   0.00924   0.00162  -0.0895   0.3155   0.0432
   2.250   0.7226   0.00923   0.00170  -0.0896   0.3101   0.0887
   2.750   0.7724   0.00755   0.00203  -0.0890   0.3016   1.0000
   3.000   0.8003   0.00766   0.00211  -0.0891   0.2972   1.0000
   3.250   0.8281   0.00780   0.00220  -0.0891   0.2928   1.0000
   3.500   0.8559   0.00791   0.00230  -0.0891   0.2890   1.0000
   3.750   0.8837   0.00803   0.00240  -0.0892   0.2848   1.0000
   4.000   0.9114   0.00816   0.00251  -0.0892   0.2806   1.0000
   4.250   0.9389   0.00831   0.00264  -0.0892   0.2756   1.0000
   4.500   0.9664   0.00844   0.00275  -0.0892   0.2693   1.0000
   4.750   0.9935   0.00863   0.00289  -0.0892   0.2607   1.0000
   5.000   1.0209   0.00877   0.00303  -0.0892   0.2546   1.0000
   5.250   1.0479   0.00897   0.00319  -0.0891   0.2456   1.0000
   5.500   1.0746   0.00918   0.00335  -0.0891   0.2344   1.0000
   5.750   1.1013   0.00940   0.00354  -0.0890   0.2230   1.0000
   6.000   1.1271   0.00973   0.00377  -0.0888   0.2051   1.0000
   6.250   1.1511   0.01029   0.00412  -0.0884   0.1677   1.0000
   6.500   1.1651   0.01224   0.00538  -0.0867   0.0493   1.0000
   6.750   1.1875   0.01301   0.00598  -0.0861   0.0163   1.0000
   7.000   1.2123   0.01340   0.00639  -0.0857   0.0126   1.0000
   7.250   1.2373   0.01375   0.00676  -0.0854   0.0106   1.0000
   7.500   1.2622   0.01408   0.00713  -0.0850   0.0097   1.0000
   7.750   1.2865   0.01448   0.00755  -0.0846   0.0087   1.0000
   8.000   1.3099   0.01498   0.00809  -0.0841   0.0074   1.0000
   8.250   1.3340   0.01535   0.00849  -0.0837   0.0070   1.0000
   8.500   1.3575   0.01577   0.00895  -0.0832   0.0064   1.0000
   8.750   1.3805   0.01623   0.00944  -0.0826   0.0059   1.0000
   9.000   1.4027   0.01675   0.00999  -0.0819   0.0055   1.0000
   9.250   1.4232   0.01743   0.01074  -0.0809   0.0050   1.0000
   9.500   1.4447   0.01795   0.01132  -0.0802   0.0049   1.0000
   9.750   1.4655   0.01851   0.01193  -0.0793   0.0046   1.0000
  10.000   1.4857   0.01909   0.01256  -0.0784   0.0043   1.0000
  10.250   1.5052   0.01968   0.01320  -0.0773   0.0041   1.0000
  10.500   1.5239   0.02030   0.01387  -0.0762   0.0038   1.0000
  10.750   1.5409   0.02103   0.01464  -0.0749   0.0036   1.0000
  11.000   1.5549   0.02192   0.01562  -0.0731   0.0034   1.0000
  11.250   1.5645   0.02295   0.01674  -0.0706   0.0033   1.0000
  11.500   1.5740   0.02380   0.01768  -0.0681   0.0032   1.0000
  11.750   1.5825   0.02477   0.01873  -0.0656   0.0032   1.0000
  12.000   1.5892   0.02590   0.01996  -0.0631   0.0031   1.0000
  12.250   1.5950   0.02716   0.02132  -0.0608   0.0030   1.0000
  12.500   1.5992   0.02862   0.02287  -0.0586   0.0029   1.0000
  12.750   1.6024   0.03027   0.02463  -0.0565   0.0028   1.0000
  13.000   1.6041   0.03218   0.02664  -0.0547   0.0028   1.0000
  13.250   1.6044   0.03439   0.02896  -0.0533   0.0027   1.0000
  13.500   1.6042   0.03687   0.03155  -0.0523   0.0027   1.0000
  13.750   1.6018   0.03985   0.03466  -0.0518   0.0026   1.0000
  14.000   1.5987   0.04319   0.03811  -0.0518   0.0026   1.0000
  14.250   1.5934   0.04708   0.04213  -0.0523   0.0025   1.0000
  14.500   1.5877   0.05123   0.04640  -0.0532   0.0025   1.0000
  14.750   1.5798   0.05594   0.05124  -0.0545   0.0025   1.0000
  15.000   1.5704   0.06097   0.05639  -0.0560   0.0024   1.0000
  15.250   1.5585   0.06630   0.06183  -0.0575   0.0024   1.0000
  15.500   1.5455   0.07177   0.06743  -0.0590   0.0024   1.0000
  15.750   1.5310   0.07748   0.07325  -0.0605   0.0024   1.0000
  16.000   1.5167   0.08319   0.07907  -0.0621   0.0024   1.0000
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