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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 500,000
Max Cl/Cd: 83.57 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe286-il-500000.txt
Download as CSV file: xf-goe286-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3863   0.09102   0.08888  -0.0142   1.0000   0.0245
  -8.000  -0.3824   0.08726   0.08514  -0.0173   1.0000   0.0256
  -7.750  -0.3811   0.08131   0.07922  -0.0280   1.0000   0.0265
  -7.500  -0.3713   0.07599   0.07389  -0.0349   1.0000   0.0266
  -7.250  -0.3660   0.07150   0.06937  -0.0384   1.0000   0.0266
  -7.000  -0.3653   0.06706   0.06496  -0.0385   0.9985   0.0271
  -6.750  -0.3389   0.06404   0.06192  -0.0421   0.9949   0.0276
  -6.500  -0.3106   0.06071   0.05855  -0.0467   0.9894   0.0285
  -6.250  -0.2789   0.05614   0.05390  -0.0535   0.9829   0.0299
  -6.000  -0.2353   0.04727   0.04458  -0.0648   0.9719   0.0327
  -5.750  -0.2230   0.04170   0.03891  -0.0665   0.9591   0.0336
  -5.500  -0.2063   0.04003   0.03718  -0.0658   0.9442   0.0341
  -5.250  -0.1888   0.03842   0.03549  -0.0651   0.9278   0.0350
  -5.000  -0.1682   0.03623   0.03317  -0.0649   0.9091   0.0366
  -4.750  -0.1428   0.02998   0.02625  -0.0660   0.8914   0.0412
  -4.500  -0.1224   0.02855   0.02474  -0.0653   0.8698   0.0419
  -4.250  -0.0999   0.02736   0.02341  -0.0648   0.8486   0.0429
  -4.000  -0.0757   0.02603   0.02187  -0.0644   0.8272   0.0449
  -3.750  -0.0492   0.02338   0.01867  -0.0642   0.8075   0.0510
  -3.500  -0.0240   0.02241   0.01762  -0.0642   0.7851   0.0524
  -3.250   0.0024   0.02151   0.01654  -0.0640   0.7601   0.0551
  -2.500   0.0887   0.01399   0.00732  -0.0626   0.6799   0.0415
  -2.250   0.1171   0.01368   0.00680  -0.0623   0.6606   0.0406
  -2.000   0.1454   0.01325   0.00622  -0.0622   0.6451   0.0403
  -1.750   0.1735   0.01259   0.00541  -0.0621   0.6323   0.0402
  -1.500   0.2016   0.01206   0.00476  -0.0620   0.6208   0.0402
  -1.250   0.2297   0.01150   0.00413  -0.0619   0.6087   0.0404
  -1.000   0.2577   0.01097   0.00354  -0.0619   0.5958   0.0409
  -0.750   0.2858   0.01057   0.00309  -0.0618   0.5841   0.0421
  -0.500   0.3142   0.01034   0.00281  -0.0618   0.5719   0.0430
  -0.250   0.3427   0.01016   0.00258  -0.0618   0.5578   0.0441
   0.000   0.3713   0.01003   0.00240  -0.0619   0.5411   0.0455
   0.250   0.3998   0.00994   0.00224  -0.0619   0.5197   0.0474
   1.000   0.4841   0.00982   0.00206  -0.0620   0.4422   0.1366
   1.250   0.5099   0.00777   0.00218  -0.0620   0.4231   1.0000
   1.500   0.5375   0.00798   0.00221  -0.0620   0.4045   1.0000
   1.750   0.5652   0.00818   0.00227  -0.0619   0.3876   1.0000
   2.250   0.6208   0.00852   0.00240  -0.0619   0.3598   1.0000
   2.500   0.6486   0.00870   0.00247  -0.0619   0.3456   1.0000
   2.750   0.6763   0.00888   0.00256  -0.0619   0.3321   1.0000
   3.000   0.7041   0.00905   0.00266  -0.0619   0.3207   1.0000
   3.250   0.7318   0.00923   0.00276  -0.0618   0.3094   1.0000
   3.500   0.7594   0.00942   0.00287  -0.0618   0.2972   1.0000
   3.750   0.7870   0.00960   0.00300  -0.0618   0.2850   1.0000
   4.000   0.8144   0.00981   0.00314  -0.0618   0.2710   1.0000
   4.250   0.8415   0.01007   0.00329  -0.0618   0.2536   1.0000
   4.500   0.8680   0.01041   0.00349  -0.0617   0.2264   1.0000
   4.750   0.8921   0.01115   0.00388  -0.0614   0.1612   1.0000
   5.000   0.9174   0.01168   0.00424  -0.0612   0.1382   1.0000
   5.250   0.9439   0.01199   0.00452  -0.0611   0.1331   1.0000
   5.500   0.9704   0.01228   0.00480  -0.0609   0.1288   1.0000
   5.750   0.9970   0.01253   0.00506  -0.0608   0.1265   1.0000
   6.000   1.0236   0.01278   0.00533  -0.0607   0.1246   1.0000
   6.250   1.0499   0.01306   0.00562  -0.0606   0.1226   1.0000
   6.500   1.0759   0.01336   0.00595  -0.0604   0.1205   1.0000
   6.750   1.1011   0.01376   0.00634  -0.0601   0.1163   1.0000
   7.000   1.1268   0.01407   0.00667  -0.0599   0.1131   1.0000
   7.250   1.1530   0.01430   0.00696  -0.0598   0.1106   1.0000
   7.500   1.1786   0.01459   0.00728  -0.0596   0.1074   1.0000
   7.750   1.2032   0.01499   0.00768  -0.0593   0.1033   1.0000
   8.000   1.2284   0.01531   0.00802  -0.0590   0.0997   1.0000
   8.250   1.2546   0.01548   0.00826  -0.0588   0.0958   1.0000
   8.500   1.2794   0.01581   0.00857  -0.0585   0.0881   1.0000
   8.750   1.3027   0.01630   0.00893  -0.0581   0.0662   1.0000
   9.000   1.3247   0.01691   0.00950  -0.0575   0.0601   1.0000
   9.250   1.3471   0.01744   0.01010  -0.0569   0.0570   1.0000
   9.500   1.3674   0.01816   0.01088  -0.0560   0.0535   1.0000
   9.750   1.3863   0.01899   0.01175  -0.0550   0.0493   1.0000
  10.000   1.4088   0.01939   0.01226  -0.0544   0.0459   1.0000
  10.250   1.4266   0.02022   0.01312  -0.0532   0.0404   1.0000
  10.500   1.4486   0.02061   0.01351  -0.0526   0.0322   1.0000
  11.000   1.4776   0.02255   0.01535  -0.0494   0.0191   1.0000
  11.250   1.4879   0.02369   0.01656  -0.0473   0.0176   1.0000
  11.500   1.4948   0.02479   0.01776  -0.0446   0.0167   1.0000
  11.750   1.5012   0.02599   0.01907  -0.0422   0.0161   1.0000
  12.000   1.5060   0.02740   0.02060  -0.0399   0.0155   1.0000
  12.250   1.5090   0.02908   0.02239  -0.0379   0.0151   1.0000
  12.500   1.5098   0.03110   0.02453  -0.0362   0.0147   1.0000
  12.750   1.5078   0.03361   0.02716  -0.0349   0.0143   1.0000
  13.000   1.5025   0.03670   0.03038  -0.0341   0.0140   1.0000
  13.250   1.4943   0.04041   0.03422  -0.0338   0.0137   1.0000
  13.500   1.4837   0.04477   0.03873  -0.0343   0.0135   1.0000
  13.750   1.4794   0.04855   0.04264  -0.0349   0.0134   1.0000
  14.000   1.4749   0.05241   0.04663  -0.0356   0.0133   1.0000
  14.250   1.4684   0.05654   0.05088  -0.0364   0.0131   1.0000
  14.500   1.4607   0.06085   0.05531  -0.0373   0.0130   1.0000
  14.750   1.4523   0.06532   0.05990  -0.0383   0.0129   1.0000
  15.000   1.4434   0.06993   0.06462  -0.0393   0.0127   1.0000
  15.250   1.4350   0.07460   0.06940  -0.0405   0.0126   1.0000
  15.500   1.4266   0.07935   0.07426  -0.0418   0.0124   1.0000
  15.750   1.4186   0.08408   0.07910  -0.0432   0.0123   1.0000
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