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GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 432 AIRFOIL (goe432-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.98 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe432-il-1000000.txt
Download as CSV file: xf-goe432-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 432 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3711   0.09598   0.09438  -0.0197   1.0000   0.0113
  -8.500  -0.3719   0.09341   0.09183  -0.0194   1.0000   0.0116
  -7.250  -0.4023   0.01877   0.01552  -0.0787   0.9848   0.0104
  -7.000  -0.3699   0.01708   0.01359  -0.0806   0.9838   0.0108
  -6.750  -0.3449   0.01591   0.01224  -0.0803   0.9804   0.0112
  -6.500  -0.3154   0.01475   0.01088  -0.0809   0.9777   0.0117
  -6.250  -0.2832   0.01365   0.00957  -0.0821   0.9757   0.0122
  -6.000  -0.2482   0.01272   0.00845  -0.0836   0.9740   0.0127
  -5.750  -0.2094   0.01199   0.00756  -0.0859   0.9726   0.0131
  -5.500  -0.1724   0.01057   0.00593  -0.0880   0.9713   0.0143
  -5.250  -0.1426   0.01019   0.00552  -0.0883   0.9676   0.0152
  -5.000  -0.1132   0.00987   0.00514  -0.0884   0.9635   0.0162
  -4.750  -0.0812   0.00951   0.00471  -0.0891   0.9605   0.0170
  -4.500  -0.0486   0.00886   0.00401  -0.0899   0.9570   0.0189
  -4.250  -0.0226   0.00863   0.00376  -0.0892   0.9491   0.0203
  -4.000   0.0084   0.00841   0.00348  -0.0896   0.9421   0.0216
  -3.750   0.0333   0.00805   0.00312  -0.0887   0.9329   0.0243
  -3.500   0.0620   0.00797   0.00304  -0.0886   0.9232   0.0266
  -3.250   0.0892   0.00766   0.00267  -0.0882   0.9097   0.0291
  -3.000   0.1170   0.00756   0.00255  -0.0879   0.8906   0.0317
  -2.750   0.1447   0.00756   0.00245  -0.0875   0.8637   0.0341
  -2.500   0.1707   0.00756   0.00231  -0.0868   0.8313   0.0358
  -2.250   0.1949   0.00738   0.00197  -0.0858   0.7992   0.0390
  -2.000   0.2194   0.00745   0.00190  -0.0848   0.7650   0.0415
  -1.750   0.2434   0.00754   0.00182  -0.0838   0.7234   0.0437
  -1.500   0.2674   0.00770   0.00179  -0.0827   0.6775   0.0450
  -1.250   0.2906   0.00764   0.00149  -0.0816   0.6267   0.0480
  -1.000   0.3145   0.00773   0.00139  -0.0807   0.5782   0.0515
  -0.750   0.3397   0.00780   0.00132  -0.0800   0.5473   0.0544
  -0.500   0.3656   0.00786   0.00127  -0.0794   0.5263   0.0568
  -0.250   0.3918   0.00785   0.00119  -0.0789   0.5099   0.0614
   0.000   0.4181   0.00784   0.00115  -0.0785   0.4953   0.0701
   0.250   0.4439   0.00771   0.00113  -0.0780   0.4815   0.1276
   0.500   0.4687   0.00743   0.00119  -0.0774   0.4682   0.2788
   0.750   0.4943   0.00729   0.00123  -0.0770   0.4546   0.3648
   1.000   0.5113   0.00636   0.00133  -0.0749   0.4424   0.7645
   1.250   0.5827   0.00609   0.00142  -0.0846   0.4228   1.0000
   1.500   0.6079   0.00620   0.00145  -0.0839   0.4096   1.0000
   1.750   0.6330   0.00633   0.00150  -0.0832   0.3952   1.0000
   2.250   0.6829   0.00663   0.00162  -0.0817   0.3628   1.0000
   2.500   0.7079   0.00678   0.00169  -0.0810   0.3491   1.0000
   2.750   0.7328   0.00694   0.00178  -0.0803   0.3350   1.0000
   3.000   0.7577   0.00711   0.00187  -0.0796   0.3195   1.0000
   3.250   0.7825   0.00728   0.00197  -0.0789   0.3040   1.0000
   3.500   0.8070   0.00749   0.00208  -0.0782   0.2824   1.0000
   3.750   0.8302   0.00782   0.00224  -0.0773   0.2471   1.0000
   4.000   0.8518   0.00832   0.00248  -0.0761   0.1973   1.0000
   4.250   0.8757   0.00861   0.00268  -0.0753   0.1834   1.0000
   4.500   0.9004   0.00882   0.00286  -0.0746   0.1767   1.0000
   4.750   0.9255   0.00900   0.00303  -0.0740   0.1732   1.0000
   5.000   0.9504   0.00920   0.00322  -0.0734   0.1698   1.0000
   5.250   0.9751   0.00942   0.00342  -0.0727   0.1660   1.0000
   5.500   0.9999   0.00963   0.00364  -0.0721   0.1631   1.0000
   5.750   1.0252   0.00978   0.00382  -0.0715   0.1616   1.0000
   6.000   1.0503   0.00994   0.00402  -0.0710   0.1596   1.0000
   6.250   1.0752   0.01014   0.00423  -0.0704   0.1568   1.0000
   6.500   1.0993   0.01041   0.00449  -0.0697   0.1517   1.0000
   6.750   1.1239   0.01062   0.00471  -0.0691   0.1478   1.0000
   7.000   1.1495   0.01073   0.00485  -0.0687   0.1434   1.0000
   7.250   1.1738   0.01096   0.00507  -0.0681   0.1370   1.0000
   7.500   1.1988   0.01114   0.00527  -0.0675   0.1320   1.0000
   7.750   1.2234   0.01133   0.00546  -0.0670   0.1250   1.0000
   8.000   1.2474   0.01158   0.00569  -0.0663   0.1153   1.0000
   8.250   1.2694   0.01201   0.00599  -0.0654   0.0955   1.0000
   8.500   1.2908   0.01249   0.00640  -0.0644   0.0824   1.0000
   8.750   1.3119   0.01299   0.00686  -0.0633   0.0717   1.0000
   9.000   1.3304   0.01371   0.00745  -0.0619   0.0495   1.0000
   9.250   1.3438   0.01489   0.00843  -0.0597   0.0228   1.0000
   9.500   1.3620   0.01560   0.00914  -0.0581   0.0171   1.0000
   9.750   1.3800   0.01631   0.00987  -0.0566   0.0142   1.0000
  10.000   1.3998   0.01681   0.01044  -0.0553   0.0131   1.0000
  10.250   1.4179   0.01743   0.01110  -0.0538   0.0120   1.0000
  10.500   1.4319   0.01838   0.01213  -0.0517   0.0107   1.0000
  10.750   1.4495   0.01895   0.01279  -0.0501   0.0103   1.0000
  11.000   1.4660   0.01957   0.01348  -0.0484   0.0098   1.0000
  11.250   1.4807   0.02026   0.01424  -0.0465   0.0093   1.0000
  11.500   1.4926   0.02095   0.01499  -0.0440   0.0088   1.0000
  11.750   1.5008   0.02179   0.01590  -0.0410   0.0084   1.0000
  12.000   1.5043   0.02292   0.01712  -0.0375   0.0080   1.0000
  12.250   1.5050   0.02424   0.01856  -0.0338   0.0076   1.0000
  12.500   1.5126   0.02518   0.01961  -0.0313   0.0075   1.0000
  12.750   1.5187   0.02626   0.02077  -0.0288   0.0073   1.0000
  13.000   1.5242   0.02744   0.02204  -0.0265   0.0071   1.0000
  13.250   1.5276   0.02882   0.02352  -0.0242   0.0069   1.0000
  13.500   1.5300   0.03036   0.02516  -0.0221   0.0067   1.0000
  13.750   1.5322   0.03204   0.02693  -0.0204   0.0065   1.0000
  14.000   1.5300   0.03426   0.02926  -0.0188   0.0064   1.0000
  14.250   1.5281   0.03666   0.03177  -0.0177   0.0062   1.0000
  14.500   1.5255   0.03935   0.03455  -0.0172   0.0061   1.0000
  14.750   1.5199   0.04266   0.03798  -0.0171   0.0060   1.0000
  15.000   1.5119   0.04657   0.04201  -0.0177   0.0059   1.0000
  15.250   1.4966   0.05188   0.04746  -0.0193   0.0058   1.0000
  15.500   1.4846   0.05707   0.05279  -0.0211   0.0058   1.0000
  15.750   1.4727   0.06243   0.05828  -0.0233   0.0057   1.0000
  16.000   1.4550   0.06877   0.06477  -0.0258   0.0057   1.0000
  16.250   1.4376   0.07516   0.07128  -0.0285   0.0057   1.0000
  16.500   1.4206   0.08169   0.07793  -0.0313   0.0057   1.0000
  16.750   1.4039   0.08830   0.08467  -0.0342   0.0056   1.0000
  17.000   1.3886   0.09492   0.09139  -0.0372   0.0057   1.0000
  17.250   1.3644   0.10317   0.09977  -0.0411   0.0055   1.0000
  17.500   1.3493   0.11005   0.10676  -0.0444   0.0055   1.0000
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