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GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 437 AIRFOIL (goe437-il)
Reynolds number: 200,000
Max Cl/Cd: 78.74 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe437-il-200000.txt
Download as CSV file: xf-goe437-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 437 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3211   0.09775   0.09438  -0.0286   1.0000   0.0315
  -7.750  -0.3263   0.09623   0.09294  -0.0286   1.0000   0.0317
  -7.500  -0.3340   0.09490   0.09170  -0.0279   1.0000   0.0319
  -7.250  -0.3355   0.09285   0.08971  -0.0287   1.0000   0.0320
  -7.000  -0.3356   0.09061   0.08751  -0.0296   1.0000   0.0321
  -6.750  -0.3345   0.08820   0.08515  -0.0304   1.0000   0.0322
  -6.500  -0.3330   0.08573   0.08272  -0.0310   1.0000   0.0323
  -6.250  -0.2903   0.06827   0.06562  -0.0238   0.9954   0.0344
  -6.000  -0.2689   0.06347   0.06080  -0.0283   0.9903   0.0358
  -5.750  -0.2451   0.05839   0.05569  -0.0348   0.9849   0.0378
  -5.500  -0.2200   0.05326   0.05052  -0.0421   0.9787   0.0402
  -5.250  -0.1715   0.04771   0.04474  -0.0596   0.9720   0.0443
  -5.000  -0.1512   0.04031   0.03732  -0.0643   0.9678   0.0459
  -4.750  -0.1310   0.03700   0.03400  -0.0647   0.9609   0.0487
  -4.500  -0.0949   0.03227   0.02914  -0.0712   0.9571   0.0527
  -4.250  -0.1144   0.04653   0.04307  -0.0713   0.9651   0.0521
  -4.000  -0.0604   0.04051   0.03654  -0.0808   0.9591   0.0588
  -3.750  -0.0265   0.03727   0.03331  -0.0841   0.9559   0.0617
  -3.500   0.0137   0.03370   0.02922  -0.0880   0.9474   0.0718
  -3.250   0.0495   0.03070   0.02624  -0.0910   0.9437   0.0757
  -3.000   0.0951   0.02172   0.01598  -0.0932   0.9392   0.0427
  -2.750   0.1311   0.01873   0.01238  -0.0944   0.9327   0.0430
  -2.500   0.1726   0.01647   0.00956  -0.0964   0.9286   0.0449
  -2.250   0.2043   0.01496   0.00793  -0.0969   0.9184   0.0535
  -2.000   0.2384   0.01355   0.00635  -0.0975   0.9095   0.0622
  -1.750   0.2732   0.01294   0.00571  -0.0984   0.9009   0.0792
  -1.500   0.3031   0.01257   0.00523  -0.0983   0.8890   0.0974
  -1.250   0.3321   0.01197   0.00469  -0.0982   0.8768   0.1184
  -1.000   0.3609   0.01147   0.00423  -0.0981   0.8641   0.1534
  -0.750   0.3891   0.01110   0.00389  -0.0978   0.8505   0.1833
  -0.500   0.4167   0.01081   0.00361  -0.0975   0.8360   0.2113
  -0.250   0.4435   0.01047   0.00337  -0.0970   0.8208   0.2528
   0.000   0.4887   0.00855   0.00317  -0.1005   0.8063   1.0000
   0.250   0.5151   0.00864   0.00302  -0.0997   0.7895   1.0000
   0.500   0.5404   0.00876   0.00295  -0.0989   0.7709   1.0000
   0.750   0.5658   0.00889   0.00291  -0.0981   0.7524   1.0000
   1.000   0.5913   0.00904   0.00288  -0.0973   0.7346   1.0000
   1.250   0.6161   0.00919   0.00291  -0.0965   0.7150   1.0000
   1.500   0.6410   0.00935   0.00294  -0.0957   0.6957   1.0000
   1.750   0.6660   0.00952   0.00297  -0.0949   0.6769   1.0000
   2.000   0.6908   0.00967   0.00303  -0.0941   0.6572   1.0000
   2.250   0.7157   0.00984   0.00309  -0.0934   0.6387   1.0000
   2.500   0.7406   0.01001   0.00319  -0.0927   0.6203   1.0000
   2.750   0.7654   0.01020   0.00329  -0.0919   0.6017   1.0000
   3.000   0.7902   0.01043   0.00342  -0.0912   0.5846   1.0000
   3.250   0.8150   0.01070   0.00358  -0.0906   0.5689   1.0000
   3.500   0.8399   0.01100   0.00379  -0.0899   0.5537   1.0000
   3.750   0.8648   0.01132   0.00407  -0.0893   0.5387   1.0000
   4.000   0.8898   0.01166   0.00436  -0.0888   0.5246   1.0000
   4.250   0.9149   0.01201   0.00467  -0.0882   0.5113   1.0000
   4.500   0.9398   0.01234   0.00501  -0.0877   0.4981   1.0000
   4.750   0.9646   0.01265   0.00539  -0.0871   0.4852   1.0000
   5.000   0.9885   0.01293   0.00566  -0.0863   0.4698   1.0000
   5.250   1.0102   0.01302   0.00580  -0.0851   0.4457   1.0000
   5.500   1.0324   0.01318   0.00596  -0.0839   0.4225   1.0000
   5.750   1.0543   0.01339   0.00617  -0.0828   0.3983   1.0000
   6.000   1.0737   0.01369   0.00639  -0.0812   0.3551   1.0000
   6.250   1.0895   0.01442   0.00679  -0.0791   0.2779   1.0000
   6.500   1.0863   0.01752   0.00840  -0.0750   0.0536   1.0000
   6.750   1.1014   0.01883   0.00965  -0.0729   0.0360   1.0000
   7.000   1.1176   0.01996   0.01097  -0.0709   0.0316   1.0000
   7.250   1.1334   0.02102   0.01223  -0.0688   0.0298   1.0000
   7.500   1.1463   0.02226   0.01362  -0.0664   0.0284   1.0000
   7.750   1.1572   0.02363   0.01510  -0.0637   0.0275   1.0000
   8.000   1.1672   0.02507   0.01664  -0.0611   0.0259   1.0000
   8.250   1.1742   0.02696   0.01854  -0.0583   0.0239   1.0000
   8.500   1.1870   0.02905   0.02065  -0.0561   0.0233   1.0000
   8.750   1.2095   0.03160   0.02325  -0.0554   0.0230   1.0000
   9.000   1.2351   0.03385   0.02560  -0.0549   0.0231   1.0000
   9.250   1.2586   0.03563   0.02759  -0.0539   0.0239   1.0000
   9.500   1.2869   0.03864   0.03111  -0.0527   0.0277   1.0000
   9.750   1.3249   0.04384   0.03654  -0.0534   0.0337   1.0000
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