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GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il)
Reynolds number: 500,000
Max Cl/Cd: 77.11 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe344-il-500000-n5.txt
Download as CSV file: xf-goe344-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.9052   0.03097   0.02753  -0.0474   1.0000   0.0120
 -10.500  -0.8948   0.02701   0.02316  -0.0469   1.0000   0.0125
 -10.250  -0.8792   0.02465   0.02047  -0.0460   1.0000   0.0131
 -10.000  -0.8593   0.02341   0.01910  -0.0452   1.0000   0.0138
  -9.750  -0.8367   0.02287   0.01851  -0.0444   1.0000   0.0145
  -9.500  -0.8143   0.02226   0.01782  -0.0437   1.0000   0.0153
  -9.250  -0.7928   0.02138   0.01679  -0.0428   1.0000   0.0162
  -9.000  -0.7717   0.02032   0.01549  -0.0418   1.0000   0.0170
  -8.750  -0.7498   0.01951   0.01456  -0.0409   1.0000   0.0177
  -8.500  -0.7264   0.01922   0.01424  -0.0402   1.0000   0.0184
  -8.250  -0.7027   0.01901   0.01399  -0.0394   1.0000   0.0192
  -8.000  -0.6794   0.01867   0.01359  -0.0386   1.0000   0.0202
  -7.750  -0.6566   0.01814   0.01294  -0.0377   1.0000   0.0212
  -7.500  -0.6337   0.01761   0.01223  -0.0367   1.0000   0.0221
  -7.250  -0.6104   0.01719   0.01168  -0.0358   1.0000   0.0226
  -7.000  -0.5886   0.01628   0.01066  -0.0349   1.0000   0.0237
  -6.750  -0.5654   0.01593   0.01028  -0.0340   1.0000   0.0245
  -6.500  -0.5422   0.01559   0.00988  -0.0331   1.0000   0.0253
  -6.250  -0.5189   0.01522   0.00945  -0.0322   1.0000   0.0262
  -6.000  -0.4882   0.01478   0.00891  -0.0329   0.9990   0.0273
  -5.750  -0.4550   0.01429   0.00830  -0.0341   0.9974   0.0282
  -5.500  -0.4205   0.01389   0.00779  -0.0356   0.9957   0.0290
  -5.250  -0.3855   0.01348   0.00729  -0.0371   0.9940   0.0295
  -5.000  -0.3533   0.01269   0.00639  -0.0381   0.9915   0.0304
  -4.750  -0.3215   0.01210   0.00576  -0.0390   0.9894   0.0316
  -4.500  -0.2894   0.01171   0.00532  -0.0399   0.9877   0.0326
  -4.250  -0.2565   0.01134   0.00491  -0.0410   0.9861   0.0333
  -4.000  -0.2249   0.01100   0.00453  -0.0418   0.9831   0.0340
  -3.750  -0.1919   0.01066   0.00416  -0.0428   0.9791   0.0348
  -3.250  -0.1257   0.01004   0.00349  -0.0449   0.9692   0.0367
  -3.000  -0.0915   0.00977   0.00320  -0.0461   0.9645   0.0378
  -2.750  -0.0617   0.00950   0.00291  -0.0463   0.9557   0.0395
  -2.500  -0.0281   0.00921   0.00264  -0.0474   0.9474   0.0427
  -2.000   0.0458   0.00866   0.00214  -0.0511   0.9198   0.0584
  -1.750   0.0792   0.00848   0.00196  -0.0521   0.9000   0.0737
  -1.500   0.1089   0.00837   0.00183  -0.0523   0.8766   0.0864
  -1.250   0.1363   0.00833   0.00174  -0.0519   0.8400   0.0990
  -1.000   0.1611   0.00845   0.00165  -0.0509   0.7695   0.1111
  -0.750   0.1856   0.00865   0.00162  -0.0499   0.7136   0.1225
  -0.500   0.2113   0.00879   0.00162  -0.0493   0.6740   0.1348
  -0.250   0.2376   0.00889   0.00161  -0.0489   0.6394   0.1445
   0.000   0.2639   0.00898   0.00160  -0.0485   0.6054   0.1534
   0.250   0.2901   0.00908   0.00160  -0.0481   0.5701   0.1653
   0.500   0.3165   0.00916   0.00161  -0.0477   0.5380   0.1809
   0.750   0.3431   0.00922   0.00164  -0.0474   0.5107   0.2016
   1.000   0.3695   0.00924   0.00170  -0.0471   0.4812   0.2488
   1.250   0.3958   0.00930   0.00176  -0.0468   0.4477   0.2967
   1.500   0.4220   0.00934   0.00183  -0.0465   0.4123   0.3523
   1.750   0.4346   0.00795   0.00196  -0.0431   0.3835   0.9329
   2.000   0.4703   0.00820   0.00210  -0.0446   0.3520   0.9766
   2.250   0.5068   0.00844   0.00222  -0.0466   0.3312   0.9884
   2.500   0.5437   0.00866   0.00235  -0.0486   0.3142   0.9950
   2.750   0.5842   0.00887   0.00249  -0.0515   0.2998   0.9996
   3.000   0.6103   0.00903   0.00259  -0.0511   0.2859   1.0000
   3.250   0.6347   0.00923   0.00269  -0.0503   0.2684   1.0000
   3.500   0.6591   0.00941   0.00281  -0.0496   0.2523   1.0000
   3.750   0.6838   0.00957   0.00292  -0.0489   0.2395   1.0000
   4.000   0.7086   0.00974   0.00305  -0.0482   0.2279   1.0000
   4.250   0.7332   0.00991   0.00319  -0.0475   0.2176   1.0000
   4.500   0.7578   0.01011   0.00335  -0.0468   0.2053   1.0000
   4.750   0.7823   0.01033   0.00351  -0.0461   0.1914   1.0000
   5.000   0.8069   0.01056   0.00370  -0.0454   0.1772   1.0000
   5.250   0.8315   0.01081   0.00390  -0.0448   0.1618   1.0000
   5.500   0.8559   0.01110   0.00413  -0.0441   0.1430   1.0000
   5.750   0.8798   0.01149   0.00441  -0.0434   0.1211   1.0000
   6.000   0.9037   0.01190   0.00473  -0.0427   0.1000   1.0000
   6.250   0.9275   0.01233   0.00508  -0.0420   0.0838   1.0000
   6.500   0.9517   0.01272   0.00544  -0.0414   0.0728   1.0000
   6.750   0.9761   0.01309   0.00580  -0.0408   0.0655   1.0000
   7.000   1.0002   0.01350   0.00620  -0.0402   0.0586   1.0000
   7.250   1.0247   0.01386   0.00657  -0.0396   0.0539   1.0000
   7.500   1.0491   0.01422   0.00695  -0.0390   0.0496   1.0000
   7.750   1.0728   0.01467   0.00740  -0.0384   0.0454   1.0000
   8.000   1.0973   0.01500   0.00780  -0.0378   0.0429   1.0000
   8.250   1.1214   0.01538   0.00821  -0.0372   0.0396   1.0000
   8.500   1.1448   0.01585   0.00868  -0.0366   0.0360   1.0000
   8.750   1.1687   0.01623   0.00912  -0.0360   0.0332   1.0000
   9.000   1.1917   0.01670   0.00959  -0.0353   0.0290   1.0000
   9.250   1.2147   0.01717   0.01011  -0.0346   0.0252   1.0000
   9.500   1.2368   0.01774   0.01068  -0.0338   0.0210   1.0000
   9.750   1.2583   0.01835   0.01131  -0.0329   0.0176   1.0000
  10.000   1.2792   0.01901   0.01201  -0.0319   0.0153   1.0000
  10.250   1.2997   0.01969   0.01275  -0.0308   0.0136   1.0000
  10.500   1.3188   0.02050   0.01362  -0.0296   0.0122   1.0000
  10.750   1.3382   0.02122   0.01446  -0.0284   0.0114   1.0000
  11.000   1.3571   0.02197   0.01531  -0.0272   0.0108   1.0000
  11.250   1.3748   0.02278   0.01622  -0.0258   0.0102   1.0000
  11.500   1.3913   0.02368   0.01721  -0.0243   0.0096   1.0000
  11.750   1.4054   0.02473   0.01835  -0.0225   0.0090   1.0000
  12.000   1.4179   0.02584   0.01958  -0.0205   0.0086   1.0000
  12.250   1.4313   0.02678   0.02064  -0.0187   0.0083   1.0000
  12.500   1.4423   0.02779   0.02179  -0.0165   0.0079   1.0000
  12.750   1.4492   0.02886   0.02298  -0.0137   0.0077   1.0000
  13.000   1.4545   0.03006   0.02429  -0.0108   0.0074   1.0000
  13.250   1.4583   0.03143   0.02578  -0.0081   0.0072   1.0000
  13.500   1.4608   0.03298   0.02746  -0.0056   0.0070   1.0000
  13.750   1.4611   0.03483   0.02944  -0.0034   0.0068   1.0000
  14.000   1.4590   0.03705   0.03179  -0.0016   0.0067   1.0000
  14.250   1.4542   0.03979   0.03468  -0.0004   0.0066   1.0000
  14.500   1.4463   0.04327   0.03831  -0.0001   0.0065   1.0000
  14.750   1.4349   0.04780   0.04301  -0.0012   0.0064   1.0000
  15.000   1.4219   0.05328   0.04866  -0.0037   0.0063   1.0000
  15.250   1.4097   0.05914   0.05471  -0.0068   0.0063   1.0000
  15.500   1.3933   0.06606   0.06181  -0.0106   0.0063   1.0000
  15.750   1.3729   0.07379   0.06971  -0.0147   0.0063   1.0000
  16.000   1.3500   0.08206   0.07813  -0.0189   0.0063   1.0000
  16.250   1.3247   0.09063   0.08685  -0.0231   0.0063   1.0000
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