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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.84 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe101-il-1000000.txt
Download as CSV file: xf-goe101-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3738   0.08609   0.08455  -0.0177   1.0000   0.0110
  -7.500  -0.3751   0.08339   0.08189  -0.0184   1.0000   0.0110
  -7.250  -0.3728   0.07994   0.07846  -0.0215   1.0000   0.0111
  -7.000  -0.3661   0.07656   0.07509  -0.0241   1.0000   0.0112
  -6.750  -0.3586   0.07288   0.07142  -0.0269   1.0000   0.0112
  -6.500  -0.3509   0.06911   0.06766  -0.0293   1.0000   0.0112
  -6.250  -0.3220   0.06315   0.06164  -0.0376   0.9967   0.0112
  -6.000  -0.3011   0.05776   0.05622  -0.0432   0.9906   0.0119
  -5.750  -0.2709   0.05446   0.05288  -0.0484   0.9849   0.0126
  -5.500  -0.2361   0.04996   0.04828  -0.0551   0.9780   0.0136
  -5.250  -0.1866   0.04370   0.04182  -0.0639   0.9701   0.0152
  -5.000  -0.1504   0.03854   0.03646  -0.0689   0.9563   0.0153
  -4.750  -0.1218   0.03331   0.03099  -0.0717   0.9367   0.0153
  -4.250  -0.0793   0.02075   0.01748  -0.0726   0.8898   0.0148
  -4.000  -0.0568   0.01685   0.01304  -0.0718   0.8657   0.0163
  -3.750  -0.0318   0.01790   0.01409  -0.0715   0.8366   0.0170
  -3.500  -0.0071   0.01686   0.01279  -0.0709   0.8073   0.0184
  -3.250   0.0180   0.01460   0.01005  -0.0699   0.7800   0.0198
  -3.000   0.0430   0.01299   0.00800  -0.0692   0.7545   0.0219
  -2.750   0.0686   0.01325   0.00827  -0.0691   0.7295   0.0234
  -2.500   0.0958   0.01471   0.00978  -0.0690   0.7070   0.0279
  -2.250   0.1223   0.01371   0.00851  -0.0684   0.6877   0.0283
  -2.000   0.1490   0.01300   0.00758  -0.0680   0.6687   0.0286
  -1.750   0.1748   0.01089   0.00512  -0.0675   0.6504   0.0300
  -1.500   0.2011   0.01007   0.00417  -0.0672   0.6304   0.0310
  -1.250   0.2277   0.00958   0.00354  -0.0668   0.6104   0.0309
  -1.000   0.2544   0.00920   0.00304  -0.0664   0.5905   0.0306
  -0.750   0.2809   0.00886   0.00260  -0.0661   0.5726   0.0308
  -0.500   0.3074   0.00855   0.00222  -0.0657   0.5552   0.0314
  -0.250   0.3340   0.00831   0.00189  -0.0654   0.5382   0.0321
   0.000   0.3608   0.00815   0.00166  -0.0651   0.5233   0.0331
   0.250   0.3878   0.00805   0.00150  -0.0649   0.5101   0.0341
   0.500   0.4149   0.00798   0.00136  -0.0647   0.4969   0.0347
   0.750   0.4420   0.00795   0.00126  -0.0645   0.4853   0.0351
   1.000   0.4693   0.00790   0.00117  -0.0643   0.4764   0.0355
   1.250   0.4966   0.00788   0.00112  -0.0641   0.4674   0.0365
   1.500   0.5239   0.00789   0.00108  -0.0640   0.4584   0.0372
   1.750   0.5513   0.00788   0.00105  -0.0638   0.4502   0.0382
   2.000   0.5786   0.00792   0.00104  -0.0636   0.4423   0.0413
   2.250   0.6102   0.00589   0.00125  -0.0652   0.4340   1.0000
   2.500   0.6371   0.00600   0.00130  -0.0650   0.4267   1.0000
   2.750   0.6641   0.00608   0.00136  -0.0648   0.4205   1.0000
   3.000   0.6910   0.00619   0.00143  -0.0645   0.4145   1.0000
   3.250   0.7182   0.00626   0.00150  -0.0644   0.4089   1.0000
   3.500   0.7450   0.00637   0.00158  -0.0642   0.4024   1.0000
   3.750   0.7721   0.00646   0.00168  -0.0640   0.3956   1.0000
   4.000   0.7988   0.00659   0.00176  -0.0637   0.3830   1.0000
   4.250   0.8255   0.00672   0.00186  -0.0635   0.3710   1.0000
   4.500   0.8520   0.00688   0.00197  -0.0633   0.3521   1.0000
   4.750   0.8777   0.00714   0.00212  -0.0630   0.3201   1.0000
   5.000   0.9012   0.00769   0.00239  -0.0624   0.2589   1.0000
   5.250   0.9234   0.00845   0.00281  -0.0617   0.1927   1.0000
   5.500   0.9476   0.00894   0.00314  -0.0612   0.1585   1.0000
   5.750   0.9694   0.00974   0.00361  -0.0604   0.0948   1.0000
   6.000   0.9925   0.01037   0.00408  -0.0598   0.0627   1.0000
   6.250   1.0135   0.01131   0.00477  -0.0588   0.0182   1.0000
   6.500   1.0376   0.01181   0.00533  -0.0582   0.0144   1.0000
   6.750   1.0622   0.01218   0.00575  -0.0577   0.0135   1.0000
   7.000   1.0862   0.01264   0.00627  -0.0571   0.0123   1.0000
   7.250   1.1096   0.01316   0.00684  -0.0564   0.0113   1.0000
   7.500   1.1305   0.01400   0.00778  -0.0554   0.0102   1.0000
   7.750   1.1504   0.01494   0.00884  -0.0542   0.0095   1.0000
   8.000   1.1740   0.01533   0.00926  -0.0536   0.0090   1.0000
   8.250   1.1953   0.01600   0.01001  -0.0527   0.0085   1.0000
   8.500   1.2159   0.01672   0.01080  -0.0517   0.0080   1.0000
   8.750   1.2356   0.01750   0.01165  -0.0506   0.0076   1.0000
   9.000   1.2546   0.01831   0.01252  -0.0494   0.0073   1.0000
   9.250   1.2719   0.01927   0.01354  -0.0481   0.0070   1.0000
   9.500   1.2834   0.02081   0.01517  -0.0459   0.0066   1.0000
   9.750   1.2872   0.02343   0.01796  -0.0428   0.0063   1.0000
  10.000   1.3042   0.02427   0.01889  -0.0415   0.0062   1.0000
  10.250   1.3192   0.02530   0.02002  -0.0399   0.0060   1.0000
  10.500   1.3326   0.02641   0.02125  -0.0381   0.0058   1.0000
  10.750   1.3429   0.02757   0.02251  -0.0359   0.0055   1.0000
  11.000   1.3490   0.02890   0.02396  -0.0332   0.0053   1.0000
  11.250   1.3541   0.03022   0.02539  -0.0306   0.0051   1.0000
  11.500   1.3568   0.03199   0.02730  -0.0280   0.0050   1.0000
  11.750   1.3595   0.03365   0.02909  -0.0259   0.0049   1.0000
  12.000   1.3591   0.03589   0.03147  -0.0239   0.0049   1.0000
  12.250   1.3580   0.03822   0.03395  -0.0223   0.0048   1.0000
  12.500   1.3547   0.04095   0.03684  -0.0210   0.0048   1.0000
  12.750   1.3538   0.04330   0.03930  -0.0205   0.0046   1.0000
  13.000   1.3461   0.04698   0.04317  -0.0201   0.0046   1.0000
  13.250   1.3411   0.05031   0.04663  -0.0204   0.0046   1.0000
  13.500   1.3338   0.05420   0.05066  -0.0211   0.0045   1.0000
  13.750   1.3249   0.05851   0.05513  -0.0224   0.0045   1.0000
  14.000   1.3107   0.06400   0.06080  -0.0242   0.0045   1.0000
  14.250   1.2926   0.07040   0.06740  -0.0268   0.0046   1.0000
  14.500   1.2751   0.07703   0.07422  -0.0299   0.0046   1.0000
  14.750   1.2384   0.08790   0.08539  -0.0353   0.0047   1.0000
  15.000   1.2279   0.09406   0.09165  -0.0389   0.0047   1.0000
  15.250   1.1959   0.10543   0.10326  -0.0455   0.0048   1.0000
  15.500   1.1654   0.11754   0.11556  -0.0528   0.0049   1.0000
  15.750   1.1549   0.12521   0.12332  -0.0577   0.0049   1.0000
  16.000   1.1150   0.14231   0.14062  -0.0682   0.0052   1.0000
  16.250   1.0836   0.15850   0.15694  -0.0778   0.0055   1.0000
  16.500   1.0353   0.18285   0.18133  -0.0905   0.0062   1.0000
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