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GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il)
Reynolds number: 200,000
Max Cl/Cd: 60.14 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe344-il-200000-n5.txt
Download as CSV file: xf-goe344-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5320   0.09733   0.09353  -0.0121   1.0000   0.0224
  -9.250  -0.5381   0.09190   0.08813  -0.0147   1.0000   0.0226
  -9.000  -0.5435   0.08751   0.08380  -0.0164   1.0000   0.0229
  -8.750  -0.5483   0.08403   0.08037  -0.0176   1.0000   0.0231
  -8.500  -0.5490   0.08080   0.07716  -0.0190   1.0000   0.0234
  -8.250  -0.5455   0.07776   0.07413  -0.0205   1.0000   0.0239
  -8.000  -0.5407   0.07470   0.07107  -0.0219   1.0000   0.0246
  -7.750  -0.5365   0.07082   0.06718  -0.0239   1.0000   0.0255
  -7.500  -0.5335   0.06541   0.06171  -0.0268   1.0000   0.0265
  -7.000  -0.5552   0.03086   0.02548  -0.0386   1.0000   0.0301
  -6.750  -0.5356   0.02991   0.02449  -0.0377   1.0000   0.0312
  -6.500  -0.5161   0.02842   0.02279  -0.0369   1.0000   0.0324
  -6.250  -0.4972   0.02613   0.02012  -0.0359   1.0000   0.0337
  -6.000  -0.4768   0.02436   0.01801  -0.0350   1.0000   0.0353
  -5.750  -0.4556   0.02265   0.01590  -0.0340   1.0000   0.0369
  -5.500  -0.4335   0.02120   0.01410  -0.0330   1.0000   0.0377
  -5.250  -0.4107   0.02001   0.01261  -0.0321   1.0000   0.0385
  -5.000  -0.3880   0.01878   0.01124  -0.0313   1.0000   0.0402
  -4.750  -0.3646   0.01810   0.01047  -0.0305   1.0000   0.0414
  -4.500  -0.3407   0.01738   0.00963  -0.0297   1.0000   0.0424
  -4.250  -0.3165   0.01672   0.00886  -0.0290   1.0000   0.0435
  -4.000  -0.2921   0.01613   0.00815  -0.0282   1.0000   0.0446
  -3.750  -0.2675   0.01560   0.00753  -0.0275   1.0000   0.0458
  -3.500  -0.2428   0.01519   0.00704  -0.0269   1.0000   0.0473
  -3.250  -0.2164   0.01478   0.00656  -0.0266   0.9996   0.0490
  -3.000  -0.1819   0.01425   0.00605  -0.0280   0.9970   0.0515
  -2.750  -0.1463   0.01389   0.00567  -0.0297   0.9944   0.0544
  -2.500  -0.1100   0.01352   0.00526  -0.0315   0.9898   0.0585
  -2.250  -0.0700   0.01311   0.00491  -0.0341   0.9850   0.0658
  -2.000  -0.0322   0.01273   0.00458  -0.0361   0.9776   0.0781
  -1.750   0.0042   0.01242   0.00435  -0.0379   0.9694   0.0955
  -1.500   0.0410   0.01217   0.00415  -0.0396   0.9602   0.1144
  -1.250   0.0776   0.01192   0.00394  -0.0413   0.9494   0.1297
  -1.000   0.1132   0.01167   0.00373  -0.0428   0.9379   0.1445
  -0.750   0.1479   0.01141   0.00355  -0.0441   0.9253   0.1620
  -0.500   0.1845   0.01111   0.00333  -0.0458   0.9114   0.1801
  -0.250   0.2224   0.01082   0.00312  -0.0477   0.8937   0.1998
   0.000   0.2572   0.01057   0.00296  -0.0489   0.8678   0.2276
   0.250   0.2906   0.01032   0.00282  -0.0498   0.8280   0.2789
   0.500   0.3208   0.01009   0.00264  -0.0499   0.7676   0.3551
   1.000   0.4137   0.00924   0.00280  -0.0566   0.6603   1.0000
   1.250   0.4375   0.00949   0.00281  -0.0555   0.6193   1.0000
   1.500   0.4611   0.00973   0.00284  -0.0544   0.5795   1.0000
   1.750   0.4846   0.00999   0.00289  -0.0534   0.5430   1.0000
   2.000   0.5081   0.01024   0.00297  -0.0524   0.5076   1.0000
   2.250   0.5317   0.01050   0.00305  -0.0514   0.4723   1.0000
   2.500   0.5552   0.01077   0.00316  -0.0504   0.4373   1.0000
   2.750   0.5786   0.01106   0.00328  -0.0494   0.4037   1.0000
   3.000   0.6022   0.01135   0.00343  -0.0485   0.3761   1.0000
   3.250   0.6260   0.01164   0.00360  -0.0477   0.3551   1.0000
   3.500   0.6500   0.01191   0.00380  -0.0468   0.3376   1.0000
   3.750   0.6741   0.01219   0.00401  -0.0460   0.3224   1.0000
   4.000   0.6981   0.01249   0.00423  -0.0453   0.3047   1.0000
   4.250   0.7220   0.01281   0.00446  -0.0445   0.2849   1.0000
   4.500   0.7462   0.01309   0.00469  -0.0438   0.2685   1.0000
   4.750   0.7709   0.01334   0.00493  -0.0431   0.2555   1.0000
   5.000   0.7955   0.01360   0.00519  -0.0424   0.2423   1.0000
   5.250   0.8201   0.01388   0.00547  -0.0418   0.2281   1.0000
   5.500   0.8447   0.01417   0.00575  -0.0412   0.2141   1.0000
   5.750   0.8691   0.01448   0.00606  -0.0405   0.1981   1.0000
   6.000   0.8931   0.01485   0.00639  -0.0398   0.1788   1.0000
   6.250   0.9170   0.01525   0.00675  -0.0392   0.1560   1.0000
   6.500   0.9401   0.01576   0.00717  -0.0384   0.1322   1.0000
   6.750   0.9628   0.01635   0.00768  -0.0376   0.1103   1.0000
   7.000   0.9851   0.01699   0.00828  -0.0367   0.0949   1.0000
   7.250   1.0076   0.01760   0.00889  -0.0359   0.0843   1.0000
   7.500   1.0300   0.01822   0.00955  -0.0350   0.0769   1.0000
   7.750   1.0517   0.01889   0.01024  -0.0340   0.0707   1.0000
   8.000   1.0736   0.01952   0.01094  -0.0331   0.0650   1.0000
   8.250   1.0953   0.02016   0.01164  -0.0322   0.0591   1.0000
   8.500   1.1159   0.02090   0.01244  -0.0312   0.0546   1.0000
   8.750   1.1377   0.02149   0.01315  -0.0303   0.0502   1.0000
   9.000   1.1575   0.02228   0.01397  -0.0292   0.0458   1.0000
   9.250   1.1780   0.02298   0.01480  -0.0281   0.0420   1.0000
   9.500   1.1982   0.02367   0.01561  -0.0271   0.0377   1.0000
   9.750   1.2167   0.02453   0.01655  -0.0258   0.0338   1.0000
  10.000   1.2355   0.02533   0.01746  -0.0246   0.0301   1.0000
  10.250   1.2514   0.02639   0.01858  -0.0230   0.0272   1.0000
  10.500   1.2679   0.02735   0.01970  -0.0215   0.0243   1.0000
  10.750   1.2824   0.02842   0.02082  -0.0199   0.0221   1.0000
  11.000   1.2945   0.02967   0.02224  -0.0179   0.0204   1.0000
  11.250   1.3054   0.03096   0.02369  -0.0157   0.0191   1.0000
  11.500   1.3141   0.03229   0.02517  -0.0134   0.0181   1.0000
  11.750   1.3190   0.03366   0.02666  -0.0106   0.0172   1.0000
  12.000   1.3194   0.03534   0.02845  -0.0075   0.0165   1.0000
  12.250   1.3182   0.03729   0.03055  -0.0046   0.0159   1.0000
  12.500   1.3187   0.03926   0.03272  -0.0024   0.0154   1.0000
  12.750   1.3174   0.04152   0.03517  -0.0006   0.0148   1.0000
  13.000   1.3146   0.04411   0.03795   0.0007   0.0143   1.0000
  13.250   1.3101   0.04713   0.04115   0.0013   0.0139   1.0000
  13.500   1.3038   0.05071   0.04492   0.0010   0.0136   1.0000
  13.750   1.2958   0.05496   0.04936  -0.0002   0.0134   1.0000
  14.000   1.2862   0.05986   0.05445  -0.0023   0.0132   1.0000
  14.250   1.2749   0.06542   0.06019  -0.0050   0.0131   1.0000
  14.500   1.2614   0.07160   0.06658  -0.0083   0.0130   1.0000
  14.750   1.2461   0.07833   0.07348  -0.0120   0.0129   1.0000
  15.000   1.2290   0.08551   0.08081  -0.0158   0.0129   1.0000
  15.250   1.2103   0.09314   0.08861  -0.0199   0.0129   1.0000
  15.500   1.1901   0.10117   0.09680  -0.0241   0.0129   1.0000
  15.750   1.1685   0.10969   0.10547  -0.0286   0.0130   1.0000
  16.000   1.1452   0.11897   0.11492  -0.0335   0.0131   1.0000
  16.250   1.1182   0.12960   0.12572  -0.0393   0.0132   1.0000
  16.500   1.0781   0.14446   0.14079  -0.0475   0.0136   1.0000
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