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GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 796 AIRFOIL (goe796-il)
Reynolds number: 200,000
Max Cl/Cd: 77.96 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe796-il-200000.txt
Download as CSV file: xf-goe796-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 796 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3883   0.10042   0.09684  -0.0481   1.0000   0.0709
  -9.250  -0.4102   0.09747   0.09398  -0.0484   1.0000   0.0711
  -9.000  -0.4333   0.09514   0.09174  -0.0470   1.0000   0.0711
  -8.750  -0.4220   0.09128   0.08790  -0.0434   1.0000   0.0719
  -8.500  -0.4267   0.08956   0.08624  -0.0402   1.0000   0.0723
  -8.250  -0.4414   0.08818   0.08492  -0.0367   1.0000   0.0726
  -8.000  -0.4545   0.08650   0.08332  -0.0344   0.9991   0.0730
  -7.750  -0.4826   0.05592   0.05227  -0.0656   0.9847   0.0509
  -7.500  -0.4764   0.04519   0.04103  -0.0718   0.9766   0.0466
  -7.250  -0.4703   0.03257   0.02713  -0.0767   0.9710   0.0442
  -7.000  -0.4466   0.02953   0.02361  -0.0776   0.9634   0.0448
  -6.750  -0.4130   0.02697   0.02061  -0.0799   0.9597   0.0458
  -6.500  -0.3756   0.02471   0.01793  -0.0825   0.9575   0.0466
  -6.250  -0.3487   0.02314   0.01606  -0.0826   0.9495   0.0475
  -6.000  -0.3109   0.02170   0.01434  -0.0848   0.9462   0.0488
  -5.750  -0.2719   0.01997   0.01246  -0.0873   0.9441   0.0514
  -5.500  -0.2417   0.01915   0.01163  -0.0880   0.9373   0.0550
  -5.250  -0.2077   0.01805   0.01046  -0.0892   0.9324   0.0632
  -5.000  -0.1697   0.01764   0.01007  -0.0912   0.9291   0.0769
  -4.750  -0.1405   0.01750   0.00986  -0.0914   0.9215   0.0862
  -4.500  -0.1070   0.01742   0.00969  -0.0924   0.9160   0.0944
  -4.250  -0.0722   0.01698   0.00923  -0.0938   0.9124   0.1015
  -4.000  -0.0471   0.01679   0.00899  -0.0932   0.9034   0.1076
  -3.750  -0.0155   0.01634   0.00851  -0.0938   0.8986   0.1158
  -3.500   0.0116   0.01616   0.00830  -0.0936   0.8911   0.1248
  -3.250   0.0400   0.01562   0.00778  -0.0936   0.8850   0.1337
  -3.000   0.0692   0.01523   0.00736  -0.0936   0.8797   0.1450
  -2.750   0.0950   0.01499   0.00713  -0.0932   0.8717   0.1574
  -2.500   0.1243   0.01457   0.00674  -0.0933   0.8669   0.1705
  -2.250   0.1494   0.01431   0.00654  -0.0927   0.8581   0.1820
  -2.000   0.1780   0.01394   0.00618  -0.0925   0.8522   0.1956
  -1.750   0.2035   0.01369   0.00598  -0.0919   0.8432   0.2108
  -1.500   0.2316   0.01331   0.00566  -0.0917   0.8370   0.2338
  -1.250   0.2563   0.01294   0.00553  -0.0911   0.8281   0.2793
  -1.000   0.2804   0.01207   0.00530  -0.0904   0.8218   0.4392
  -0.750   0.2941   0.01097   0.00544  -0.0868   0.8131   0.7702
  -0.500   0.3737   0.01069   0.00534  -0.0959   0.8075   0.9867
  -0.250   0.4190   0.01067   0.00519  -0.0996   0.7990   1.0000
   0.000   0.4446   0.01067   0.00506  -0.0990   0.7920   1.0000
   0.250   0.4690   0.01075   0.00505  -0.0983   0.7842   1.0000
   0.500   0.4947   0.01079   0.00498  -0.0978   0.7773   1.0000
   0.750   0.5194   0.01088   0.00500  -0.0971   0.7696   1.0000
   1.000   0.5450   0.01094   0.00496  -0.0965   0.7621   1.0000
   1.250   0.5699   0.01103   0.00500  -0.0958   0.7541   1.0000
   1.500   0.5956   0.01111   0.00500  -0.0953   0.7465   1.0000
   1.750   0.6205   0.01122   0.00507  -0.0946   0.7385   1.0000
   2.000   0.6463   0.01130   0.00507  -0.0940   0.7303   1.0000
   2.250   0.6707   0.01141   0.00515  -0.0932   0.7208   1.0000
   2.500   0.6970   0.01147   0.00512  -0.0926   0.7120   1.0000
   2.750   0.7210   0.01156   0.00520  -0.0917   0.7009   1.0000
   3.000   0.7459   0.01165   0.00527  -0.0910   0.6906   1.0000
   3.250   0.7722   0.01173   0.00526  -0.0904   0.6812   1.0000
   3.500   0.7962   0.01182   0.00537  -0.0895   0.6693   1.0000
   3.750   0.8208   0.01191   0.00546  -0.0888   0.6575   1.0000
   4.000   0.8458   0.01199   0.00551  -0.0880   0.6455   1.0000
   4.250   0.8707   0.01207   0.00555  -0.0872   0.6324   1.0000
   4.500   0.8950   0.01215   0.00561  -0.0864   0.6176   1.0000
   4.750   0.9187   0.01225   0.00571  -0.0854   0.6010   1.0000
   5.000   0.9422   0.01237   0.00582  -0.0844   0.5829   1.0000
   5.250   0.9655   0.01253   0.00594  -0.0834   0.5635   1.0000
   5.500   0.9883   0.01272   0.00606  -0.0823   0.5423   1.0000
   5.750   1.0103   0.01296   0.00625  -0.0812   0.5189   1.0000
   6.000   1.0322   0.01327   0.00646  -0.0800   0.4972   1.0000
   6.250   1.0538   0.01361   0.00672  -0.0788   0.4757   1.0000
   6.500   1.0745   0.01400   0.00703  -0.0775   0.4538   1.0000
   6.750   1.0947   0.01443   0.00735  -0.0761   0.4326   1.0000
   7.000   1.1151   0.01485   0.00772  -0.0749   0.4138   1.0000
   7.250   1.1357   0.01530   0.00812  -0.0736   0.3973   1.0000
   7.500   1.1559   0.01576   0.00856  -0.0724   0.3818   1.0000
   7.750   1.1758   0.01623   0.00901  -0.0711   0.3668   1.0000
   8.000   1.1950   0.01672   0.00949  -0.0697   0.3515   1.0000
   8.250   1.2130   0.01723   0.00999  -0.0681   0.3348   1.0000
   8.500   1.2295   0.01777   0.01053  -0.0663   0.3165   1.0000
   8.750   1.2442   0.01836   0.01108  -0.0642   0.2969   1.0000
   9.000   1.2579   0.01892   0.01164  -0.0620   0.2748   1.0000
   9.250   1.2681   0.01954   0.01221  -0.0592   0.2519   1.0000
   9.500   1.2778   0.02025   0.01287  -0.0564   0.2289   1.0000
   9.750   1.2856   0.02115   0.01367  -0.0536   0.2087   1.0000
  10.000   1.2931   0.02218   0.01460  -0.0509   0.1920   1.0000
  10.250   1.3000   0.02334   0.01567  -0.0483   0.1782   1.0000
  10.500   1.3079   0.02450   0.01681  -0.0459   0.1658   1.0000
  10.750   1.3175   0.02560   0.01794  -0.0439   0.1543   1.0000
  11.000   1.3264   0.02678   0.01914  -0.0419   0.1439   1.0000
  11.250   1.3331   0.02812   0.02046  -0.0399   0.1344   1.0000
  11.500   1.3451   0.02914   0.02160  -0.0385   0.1243   1.0000
  11.750   1.3543   0.03040   0.02291  -0.0369   0.1155   1.0000
  12.000   1.3604   0.03191   0.02440  -0.0352   0.1073   1.0000
  12.250   1.3698   0.03325   0.02582  -0.0339   0.0983   1.0000
  12.500   1.3752   0.03494   0.02755  -0.0324   0.0899   1.0000
  12.750   1.3757   0.03711   0.02968  -0.0308   0.0819   1.0000
  13.000   1.3786   0.03918   0.03185  -0.0295   0.0730   1.0000
  13.250   1.3776   0.04168   0.03440  -0.0281   0.0647   1.0000
  13.500   1.3713   0.04474   0.03745  -0.0267   0.0585   1.0000
  13.750   1.3711   0.04734   0.04015  -0.0258   0.0524   1.0000
  14.000   1.3649   0.05058   0.04340  -0.0247   0.0483   1.0000
  14.250   1.3655   0.05327   0.04621  -0.0241   0.0441   1.0000
  14.500   1.3596   0.05669   0.04963  -0.0236   0.0413   1.0000
  14.750   1.3581   0.05974   0.05280  -0.0232   0.0387   1.0000
  15.000   1.3569   0.06286   0.05602  -0.0230   0.0364   1.0000
  15.250   1.3534   0.06630   0.05951  -0.0230   0.0347   1.0000
  15.500   1.3474   0.06992   0.06314  -0.0227   0.0332   1.0000
  15.750   1.3465   0.07322   0.06663  -0.0228   0.0319   1.0000
  16.000   1.3446   0.07667   0.07021  -0.0230   0.0306   1.0000
  16.250   1.3423   0.08023   0.07386  -0.0235   0.0294   1.0000
  16.500   1.3392   0.08388   0.07755  -0.0240   0.0284   1.0000
  16.750   1.3369   0.08707   0.08072  -0.0236   0.0272   1.0000
  17.000   1.3337   0.09105   0.08489  -0.0245   0.0265   1.0000
  17.250   1.3301   0.09507   0.08908  -0.0254   0.0258   1.0000
  17.500   1.3266   0.09907   0.09323  -0.0263   0.0251   1.0000
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