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GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il)
Reynolds number: 500,000
Max Cl/Cd: 80.62 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe344-il-500000.txt
Download as CSV file: xf-goe344-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 344 (PFALZ 71) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5213   0.08489   0.08257  -0.0141   1.0000   0.0293
  -8.000  -0.5219   0.08161   0.07931  -0.0155   1.0000   0.0300
  -7.750  -0.5205   0.07783   0.07553  -0.0177   1.0000   0.0310
  -7.500  -0.5172   0.07037   0.06800  -0.0256   1.0000   0.0338
  -7.250  -0.5769   0.03383   0.03039  -0.0367   1.0000   0.0271
  -7.000  -0.5787   0.02494   0.02058  -0.0354   1.0000   0.0280
  -6.750  -0.5593   0.02375   0.01929  -0.0343   1.0000   0.0289
  -6.500  -0.5381   0.02316   0.01868  -0.0332   1.0000   0.0298
  -6.250  -0.5173   0.02227   0.01766  -0.0321   1.0000   0.0311
  -6.000  -0.4972   0.02071   0.01581  -0.0309   1.0000   0.0323
  -5.750  -0.4761   0.01937   0.01418  -0.0296   1.0000   0.0332
  -5.500  -0.4539   0.01870   0.01330  -0.0284   1.0000   0.0338
  -5.250  -0.4328   0.01622   0.01048  -0.0275   1.0000   0.0353
  -5.000  -0.4098   0.01548   0.00967  -0.0266   1.0000   0.0365
  -4.750  -0.3863   0.01484   0.00894  -0.0258   1.0000   0.0374
  -4.500  -0.3623   0.01426   0.00826  -0.0249   1.0000   0.0384
  -4.250  -0.3380   0.01380   0.00773  -0.0242   1.0000   0.0397
  -4.000  -0.3129   0.01334   0.00719  -0.0236   1.0000   0.0407
  -3.750  -0.2872   0.01290   0.00665  -0.0230   1.0000   0.0415
  -3.500  -0.2582   0.01253   0.00622  -0.0232   0.9995   0.0422
  -3.250  -0.2197   0.01160   0.00523  -0.0255   0.9975   0.0442
  -3.000  -0.1795   0.01118   0.00481  -0.0281   0.9951   0.0467
  -2.750  -0.1411   0.01081   0.00444  -0.0302   0.9923   0.0488
  -2.500  -0.1027   0.01046   0.00407  -0.0324   0.9886   0.0513
  -2.250  -0.0623   0.01001   0.00365  -0.0350   0.9856   0.0565
  -2.000  -0.0229   0.00964   0.00334  -0.0373   0.9818   0.0671
  -1.750   0.0132   0.00926   0.00311  -0.0390   0.9766   0.0948
  -1.500   0.0525   0.00905   0.00298  -0.0414   0.9731   0.1162
  -1.250   0.0868   0.00886   0.00284  -0.0426   0.9668   0.1302
  -1.000   0.1241   0.00863   0.00266  -0.0445   0.9610   0.1431
  -0.750   0.1575   0.00839   0.00247  -0.0455   0.9520   0.1551
  -0.500   0.1928   0.00814   0.00229  -0.0469   0.9421   0.1693
  -0.250   0.2287   0.00788   0.00209  -0.0484   0.9279   0.1866
   0.000   0.2635   0.00763   0.00194  -0.0496   0.9071   0.2138
   0.250   0.2937   0.00740   0.00187  -0.0499   0.8788   0.2814
   0.500   0.3196   0.00714   0.00182  -0.0493   0.8325   0.3875
   0.750   0.3358   0.00589   0.00190  -0.0458   0.7606   0.9633
   1.000   0.3868   0.00639   0.00205  -0.0506   0.6967   0.9916
   1.250   0.4374   0.00679   0.00217  -0.0556   0.6424   1.0000
   1.500   0.4617   0.00700   0.00218  -0.0547   0.5987   1.0000
   1.750   0.4859   0.00723   0.00221  -0.0539   0.5569   1.0000
   2.000   0.5099   0.00747   0.00226  -0.0530   0.5160   1.0000
   2.250   0.5339   0.00771   0.00231  -0.0521   0.4748   1.0000
   2.500   0.5577   0.00798   0.00238  -0.0512   0.4293   1.0000
   2.750   0.5814   0.00826   0.00247  -0.0503   0.3874   1.0000
   3.000   0.6051   0.00855   0.00259  -0.0495   0.3556   1.0000
   3.250   0.6289   0.00882   0.00272  -0.0486   0.3297   1.0000
   3.500   0.6531   0.00905   0.00285  -0.0478   0.3105   1.0000
   3.750   0.6775   0.00924   0.00299  -0.0471   0.2970   1.0000
   4.000   0.7020   0.00943   0.00313  -0.0463   0.2841   1.0000
   4.250   0.7265   0.00962   0.00329  -0.0456   0.2723   1.0000
   4.500   0.7510   0.00982   0.00345  -0.0449   0.2600   1.0000
   4.750   0.7758   0.00998   0.00360  -0.0442   0.2478   1.0000
   5.000   0.8005   0.01017   0.00377  -0.0435   0.2361   1.0000
   5.250   0.8253   0.01037   0.00395  -0.0428   0.2238   1.0000
   5.500   0.8500   0.01059   0.00415  -0.0422   0.2092   1.0000
   5.750   0.8747   0.01085   0.00435  -0.0415   0.1913   1.0000
   6.000   0.8990   0.01117   0.00458  -0.0409   0.1695   1.0000
   6.250   0.9226   0.01161   0.00488  -0.0401   0.1365   1.0000
   6.500   0.9447   0.01229   0.00534  -0.0392   0.0995   1.0000
   6.750   0.9677   0.01287   0.00581  -0.0384   0.0810   1.0000
   7.000   0.9913   0.01335   0.00628  -0.0377   0.0713   1.0000
   7.250   1.0143   0.01393   0.00683  -0.0368   0.0637   1.0000
   7.500   1.0386   0.01431   0.00726  -0.0362   0.0590   1.0000
   7.750   1.0605   0.01503   0.00796  -0.0352   0.0530   1.0000
   8.000   1.0853   0.01532   0.00832  -0.0347   0.0499   1.0000
   8.250   1.1086   0.01581   0.00883  -0.0340   0.0456   1.0000
   8.500   1.1306   0.01645   0.00953  -0.0331   0.0416   1.0000
   8.750   1.1545   0.01685   0.00996  -0.0324   0.0377   1.0000
   9.000   1.1751   0.01763   0.01076  -0.0313   0.0336   1.0000
   9.250   1.1985   0.01806   0.01124  -0.0307   0.0304   1.0000
   9.500   1.2164   0.01912   0.01232  -0.0292   0.0272   1.0000
   9.750   1.2387   0.01963   0.01293  -0.0283   0.0254   1.0000
  10.000   1.2599   0.02023   0.01359  -0.0274   0.0235   1.0000
  10.250   1.2740   0.02157   0.01497  -0.0254   0.0215   1.0000
  10.500   1.2949   0.02215   0.01566  -0.0244   0.0205   1.0000
  10.750   1.3133   0.02295   0.01656  -0.0231   0.0194   1.0000
  11.000   1.3305   0.02380   0.01748  -0.0216   0.0184   1.0000
  11.250   1.3442   0.02493   0.01868  -0.0197   0.0176   1.0000
  11.500   1.3500   0.02679   0.02067  -0.0168   0.0168   1.0000
  11.750   1.3633   0.02781   0.02183  -0.0148   0.0164   1.0000
  12.000   1.3741   0.02894   0.02309  -0.0126   0.0158   1.0000
  12.250   1.3810   0.03009   0.02438  -0.0098   0.0153   1.0000
  12.500   1.3867   0.03128   0.02567  -0.0070   0.0148   1.0000
  12.750   1.3913   0.03261   0.02710  -0.0044   0.0144   1.0000
  13.000   1.3940   0.03415   0.02873  -0.0020   0.0140   1.0000
  13.250   1.3927   0.03619   0.03089   0.0004   0.0137   1.0000
  13.500   1.3852   0.03904   0.03388   0.0025   0.0134   1.0000
  13.750   1.3718   0.04288   0.03791   0.0041   0.0132   1.0000
  14.000   1.3671   0.04607   0.04128   0.0044   0.0130   1.0000
  14.250   1.3621   0.04965   0.04505   0.0039   0.0129   1.0000
  14.500   1.3553   0.05387   0.04945   0.0025   0.0128   1.0000
  14.750   1.3458   0.05880   0.05457   0.0003   0.0127   1.0000
  15.000   1.3343   0.06437   0.06032  -0.0024   0.0126   1.0000
  15.250   1.3207   0.07050   0.06663  -0.0057   0.0125   1.0000
  15.500   1.3046   0.07723   0.07354  -0.0093   0.0125   1.0000
  15.750   1.2867   0.08442   0.08088  -0.0132   0.0125   1.0000
  16.000   1.2669   0.09212   0.08875  -0.0173   0.0125   1.0000
  16.250   1.2462   0.10020   0.09698  -0.0217   0.0125   1.0000
  16.500   1.2241   0.10875   0.10568  -0.0264   0.0126   1.0000
  16.750   1.2009   0.11789   0.11496  -0.0315   0.0126   1.0000
  17.000   1.1764   0.12763   0.12484  -0.0369   0.0127   1.0000
  17.250   1.1497   0.13841   0.13577  -0.0431   0.0128   1.0000
  17.500   1.1170   0.15136   0.14886  -0.0506   0.0130   1.0000
  17.750   1.0781   0.16746   0.16512  -0.0599   0.0132   1.0000
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