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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.27 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe286-il-1000000.txt
Download as CSV file: xf-goe286-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 286 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  -0.3131   0.08054   0.07910  -0.0218   1.0000   0.0181
  -8.500  -0.3059   0.07783   0.07640  -0.0225   1.0000   0.0184
  -8.250  -0.4168   0.08332   0.08183  -0.0194   1.0000   0.0179
  -8.000  -0.4073   0.08096   0.07949  -0.0208   1.0000   0.0181
  -7.500  -0.3738   0.07478   0.07329  -0.0288   0.9799   0.0188
  -7.250  -0.3612   0.07116   0.06964  -0.0327   0.9644   0.0194
  -7.000  -0.3489   0.06684   0.06526  -0.0372   0.9496   0.0206
  -6.750  -0.3255   0.05692   0.05517  -0.0493   0.9370   0.0216
  -6.500  -0.3152   0.04665   0.04467  -0.0560   0.9243   0.0221
  -6.250  -0.2986   0.04500   0.04292  -0.0560   0.8996   0.0224
  -6.000  -0.2804   0.04323   0.04098  -0.0561   0.8672   0.0227
  -5.750  -0.2594   0.04107   0.03863  -0.0568   0.8401   0.0231
  -5.500  -0.2365   0.03843   0.03579  -0.0579   0.8194   0.0239
  -5.250  -0.2128   0.02571   0.02215  -0.0610   0.8100   0.0272
  -5.000  -0.1884   0.02458   0.02090  -0.0611   0.7898   0.0276
  -4.750  -0.1629   0.02360   0.01978  -0.0613   0.7653   0.0280
  -4.500  -0.1371   0.02251   0.01848  -0.0614   0.7327   0.0286
  -4.250  -0.1109   0.02129   0.01696  -0.0614   0.6884   0.0296
  -4.000  -0.0815   0.02128   0.01661  -0.0611   0.6581   0.0325
  -3.750  -0.0568   0.01706   0.01181  -0.0615   0.6430   0.0341
  -3.500  -0.0292   0.01637   0.01105  -0.0616   0.6301   0.0348
  -3.250  -0.0013   0.01574   0.01030  -0.0617   0.6197   0.0358
  -3.000   0.0279   0.01298   0.00705  -0.0613   0.6113   0.0302
  -2.750   0.0563   0.01196   0.00582  -0.0612   0.6023   0.0296
  -2.500   0.0849   0.01141   0.00517  -0.0612   0.5936   0.0299
  -2.250   0.1135   0.01094   0.00461  -0.0612   0.5849   0.0303
  -2.000   0.1421   0.01051   0.00409  -0.0612   0.5747   0.0306
  -1.750   0.1707   0.01014   0.00367  -0.0613   0.5641   0.0309
  -1.500   0.1993   0.00985   0.00331  -0.0613   0.5505   0.0312
  -1.250   0.2278   0.00962   0.00300  -0.0613   0.5321   0.0315
  -1.000   0.2563   0.00944   0.00271  -0.0614   0.5073   0.0317
  -0.750   0.2846   0.00936   0.00248  -0.0614   0.4711   0.0320
  -0.500   0.3128   0.00935   0.00231  -0.0615   0.4393   0.0323
  -0.250   0.3412   0.00939   0.00224  -0.0616   0.4160   0.0327
   0.000   0.3697   0.00921   0.00196  -0.0617   0.3980   0.0337
   0.250   0.3982   0.00916   0.00183  -0.0618   0.3812   0.0350
   0.500   0.4266   0.00919   0.00177  -0.0619   0.3616   0.0364
   0.750   0.4550   0.00926   0.00173  -0.0620   0.3415   0.0377
   1.000   0.4834   0.00932   0.00171  -0.0620   0.3246   0.0392
   1.250   0.5118   0.00938   0.00171  -0.0621   0.3094   0.0428
   1.500   0.5401   0.00934   0.00176  -0.0623   0.2937   0.0962
   1.750   0.5665   0.00823   0.00194  -0.0628   0.2772   0.6311
   2.000   0.5921   0.00757   0.00203  -0.0622   0.2478   1.0000
   2.250   0.6192   0.00797   0.00218  -0.0622   0.2068   1.0000
   2.500   0.6447   0.00871   0.00253  -0.0621   0.1277   1.0000
   2.750   0.6727   0.00888   0.00265  -0.0621   0.1240   1.0000
   3.000   0.7005   0.00906   0.00278  -0.0621   0.1207   1.0000
   3.250   0.7284   0.00925   0.00291  -0.0621   0.1171   1.0000
   3.500   0.7562   0.00942   0.00306  -0.0621   0.1142   1.0000
   3.750   0.7841   0.00956   0.00318  -0.0622   0.1134   1.0000
   4.000   0.8120   0.00970   0.00331  -0.0622   0.1125   1.0000
   4.250   0.8398   0.00985   0.00346  -0.0622   0.1115   1.0000
   4.500   0.8674   0.01002   0.00361  -0.0622   0.1101   1.0000
   4.750   0.8950   0.01020   0.00378  -0.0622   0.1086   1.0000
   5.000   0.9224   0.01040   0.00396  -0.0622   0.1067   1.0000
   5.250   0.9496   0.01061   0.00415  -0.0622   0.1044   1.0000
   5.500   0.9767   0.01083   0.00438  -0.0622   0.1017   1.0000
   5.750   1.0041   0.01100   0.00454  -0.0622   0.1003   1.0000
   6.000   1.0317   0.01111   0.00465  -0.0622   0.0991   1.0000
   6.250   1.0591   0.01125   0.00479  -0.0622   0.0955   1.0000
   6.500   1.0858   0.01148   0.00498  -0.0622   0.0901   1.0000
   6.750   1.1127   0.01168   0.00517  -0.0621   0.0848   1.0000
   7.000   1.1375   0.01218   0.00549  -0.0618   0.0596   1.0000
   7.250   1.1634   0.01250   0.00582  -0.0617   0.0567   1.0000
   7.500   1.1888   0.01289   0.00621  -0.0614   0.0540   1.0000
   7.750   1.2142   0.01325   0.00658  -0.0612   0.0516   1.0000
   8.000   1.2394   0.01361   0.00697  -0.0609   0.0497   1.0000
   8.250   1.2648   0.01391   0.00731  -0.0607   0.0487   1.0000
   8.500   1.2902   0.01420   0.00763  -0.0605   0.0477   1.0000
   8.750   1.3152   0.01451   0.00798  -0.0602   0.0460   1.0000
   9.000   1.3393   0.01493   0.00842  -0.0599   0.0433   1.0000
   9.250   1.3628   0.01539   0.00890  -0.0594   0.0398   1.0000
   9.500   1.3882   0.01559   0.00909  -0.0592   0.0349   1.0000
   9.750   1.4072   0.01649   0.00980  -0.0582   0.0171   1.0000
  10.000   1.4279   0.01715   0.01050  -0.0574   0.0151   1.0000
  10.250   1.4477   0.01789   0.01127  -0.0564   0.0134   1.0000
  10.500   1.4684   0.01846   0.01191  -0.0556   0.0128   1.0000
  10.750   1.4877   0.01912   0.01263  -0.0546   0.0122   1.0000
  11.000   1.5054   0.01988   0.01346  -0.0533   0.0116   1.0000
  11.250   1.5203   0.02080   0.01445  -0.0518   0.0110   1.0000
  11.500   1.5298   0.02204   0.01579  -0.0495   0.0105   1.0000
  11.750   1.5432   0.02278   0.01659  -0.0477   0.0103   1.0000
  12.000   1.5524   0.02365   0.01754  -0.0453   0.0100   1.0000
  12.250   1.5604   0.02470   0.01868  -0.0430   0.0098   1.0000
  12.500   1.5677   0.02588   0.01994  -0.0410   0.0095   1.0000
  12.750   1.5740   0.02724   0.02138  -0.0392   0.0092   1.0000
  13.000   1.5791   0.02881   0.02303  -0.0376   0.0090   1.0000
  13.250   1.5827   0.03066   0.02497  -0.0363   0.0088   1.0000
  13.500   1.5836   0.03294   0.02735  -0.0353   0.0085   1.0000
  13.750   1.5801   0.03589   0.03040  -0.0346   0.0084   1.0000
  14.000   1.5722   0.03960   0.03424  -0.0345   0.0082   1.0000
  14.250   1.5597   0.04426   0.03905  -0.0351   0.0081   1.0000
  14.500   1.5472   0.04915   0.04409  -0.0361   0.0080   1.0000
  14.750   1.5444   0.05281   0.04785  -0.0368   0.0079   1.0000
  15.000   1.5388   0.05684   0.05198  -0.0377   0.0078   1.0000
  15.250   1.5309   0.06121   0.05646  -0.0386   0.0078   1.0000
  15.500   1.5216   0.06589   0.06126  -0.0398   0.0077   1.0000
  15.750   1.5117   0.07077   0.06624  -0.0411   0.0077   1.0000
  16.000   1.5009   0.07592   0.07150  -0.0426   0.0076   1.0000
  16.250   1.4894   0.08126   0.07695  -0.0443   0.0076   1.0000
  16.500   1.4784   0.08657   0.08236  -0.0460   0.0075   1.0000
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