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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 200,000
Max Cl/Cd: 74.57 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe133-il-200000.txt
Download as CSV file: xf-goe133-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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  -0.3692   0.09408   0.09062  -0.0198   1.0000   0.0380
  -7.750  -0.3711   0.09178   0.08839  -0.0234   1.0000   0.0389
  -7.500  -0.3682   0.08892   0.08558  -0.0300   1.0000   0.0393
  -7.250  -0.3623   0.08563   0.08230  -0.0350   1.0000   0.0395
  -7.000  -0.3560   0.08222   0.07889  -0.0383   1.0000   0.0396
  -6.750  -0.3573   0.07711   0.07384  -0.0367   1.0000   0.0401
  -6.500  -0.3554   0.07415   0.07093  -0.0333   1.0000   0.0407
  -6.250  -0.3518   0.07160   0.06841  -0.0316   1.0000   0.0414
  -6.000  -0.3473   0.06917   0.06600  -0.0307   1.0000   0.0425
  -5.750  -0.3414   0.06656   0.06340  -0.0309   1.0000   0.0441
  -5.500  -0.3325   0.06359   0.06040  -0.0322   1.0000   0.0463
  -5.250  -0.3034   0.06032   0.05681  -0.0400   1.0000   0.0498
  -5.000  -0.2872   0.05747   0.05374  -0.0413   1.0000   0.0501
  -4.750  -0.2674   0.05031   0.04666  -0.0447   0.9972   0.0516
  -4.500  -0.2343   0.04681   0.04314  -0.0484   0.9933   0.0535
  -4.250  -0.1946   0.04316   0.03931  -0.0534   0.9883   0.0574
  -4.000  -0.1433   0.03782   0.03343  -0.0607   0.9843   0.0647
  -3.750  -0.1101   0.03542   0.03107  -0.0634   0.9785   0.0693
  -3.500  -0.0644   0.03172   0.02688  -0.0681   0.9737   0.0792
  -3.250  -0.0222   0.02939   0.02443  -0.0718   0.9704   0.0870
  -3.000   0.0237   0.02366   0.01750  -0.0733   0.9638   0.0633
  -2.750   0.0667   0.02081   0.01424  -0.0761   0.9595   0.0626
  -2.500   0.1104   0.01799   0.01116  -0.0796   0.9566   0.0671
  -2.250   0.1462   0.01694   0.00994  -0.0808   0.9477   0.0725
  -2.000   0.1880   0.01596   0.00867  -0.0829   0.9421   0.0765
  -1.750   0.2201   0.01467   0.00738  -0.0835   0.9309   0.0821
  -1.500   0.2526   0.01392   0.00656  -0.0838   0.9192   0.0862
  -1.250   0.2834   0.01346   0.00601  -0.0837   0.9060   0.0912
  -1.000   0.3114   0.01257   0.00519  -0.0833   0.8907   0.0963
  -0.750   0.3388   0.01210   0.00470  -0.0825   0.8724   0.1024
  -0.500   0.3655   0.01161   0.00421  -0.0815   0.8517   0.1111
  -0.250   0.3914   0.01126   0.00381  -0.0805   0.8257   0.1220
   0.000   0.4171   0.01088   0.00343  -0.0795   0.7969   0.1463
   0.250   0.4411   0.00849   0.00316  -0.0780   0.7679   1.0000
   0.500   0.4668   0.00864   0.00300  -0.0770   0.7373   1.0000
   0.750   0.4926   0.00883   0.00293  -0.0762   0.7079   1.0000
   1.000   0.5185   0.00904   0.00290  -0.0755   0.6802   1.0000
   1.250   0.5446   0.00926   0.00290  -0.0749   0.6549   1.0000
   1.500   0.5709   0.00947   0.00293  -0.0744   0.6324   1.0000
   1.750   0.5974   0.00969   0.00299  -0.0740   0.6141   1.0000
   2.000   0.6241   0.00991   0.00307  -0.0737   0.5973   1.0000
   2.250   0.6507   0.01013   0.00318  -0.0733   0.5817   1.0000
   2.500   0.6774   0.01037   0.00330  -0.0730   0.5671   1.0000
   2.750   0.7040   0.01061   0.00345  -0.0727   0.5534   1.0000
   3.000   0.7307   0.01085   0.00360  -0.0723   0.5399   1.0000
   3.250   0.7573   0.01108   0.00378  -0.0721   0.5267   1.0000
   3.500   0.7840   0.01131   0.00398  -0.0718   0.5140   1.0000
   3.750   0.8105   0.01155   0.00420  -0.0715   0.5013   1.0000
   4.000   0.8369   0.01180   0.00441  -0.0711   0.4881   1.0000
   4.250   0.8630   0.01203   0.00462  -0.0708   0.4730   1.0000
   4.500   0.8888   0.01225   0.00483  -0.0703   0.4557   1.0000
   4.750   0.9143   0.01248   0.00503  -0.0699   0.4371   1.0000
   5.000   0.9396   0.01273   0.00524  -0.0694   0.4175   1.0000
   5.250   0.9648   0.01297   0.00548  -0.0689   0.3943   1.0000
   5.500   0.9895   0.01327   0.00574  -0.0683   0.3681   1.0000
   5.750   1.0138   0.01363   0.00602  -0.0677   0.3406   1.0000
   6.000   1.0376   0.01406   0.00634  -0.0671   0.3153   1.0000
   6.250   1.0617   0.01451   0.00672  -0.0666   0.2946   1.0000
   6.500   1.0857   0.01498   0.00717  -0.0660   0.2790   1.0000
   6.750   1.1096   0.01547   0.00763  -0.0655   0.2657   1.0000
   7.000   1.1334   0.01596   0.00813  -0.0649   0.2541   1.0000
   7.250   1.1568   0.01650   0.00866  -0.0643   0.2436   1.0000
   7.500   1.1801   0.01700   0.00919  -0.0637   0.2309   1.0000
   7.750   1.2031   0.01749   0.00972  -0.0631   0.2171   1.0000
   8.000   1.2254   0.01802   0.01029  -0.0624   0.2011   1.0000
   8.250   1.2480   0.01848   0.01087  -0.0617   0.1785   1.0000
   8.500   1.2684   0.01919   0.01151  -0.0607   0.1425   1.0000
   9.000   1.3015   0.02151   0.01345  -0.0580   0.0927   1.0000
   9.250   1.3140   0.02299   0.01489  -0.0561   0.0837   1.0000
   9.500   1.3291   0.02418   0.01622  -0.0544   0.0769   1.0000
   9.750   1.3376   0.02598   0.01798  -0.0521   0.0706   1.0000
  10.000   1.3530   0.02703   0.01922  -0.0506   0.0649   1.0000
  10.250   1.3622   0.02861   0.02080  -0.0484   0.0593   1.0000
  10.500   1.3726   0.02999   0.02234  -0.0463   0.0540   1.0000
  10.750   1.3800   0.03125   0.02365  -0.0439   0.0492   1.0000
  11.000   1.3849   0.03309   0.02560  -0.0414   0.0450   1.0000
  11.250   1.3918   0.03454   0.02717  -0.0392   0.0413   1.0000
  11.500   1.3957   0.03644   0.02908  -0.0372   0.0386   1.0000
  11.750   1.4000   0.03869   0.03148  -0.0351   0.0362   1.0000
  12.000   1.4043   0.04053   0.03351  -0.0334   0.0340   1.0000
  12.250   1.4077   0.04246   0.03554  -0.0320   0.0321   1.0000
  12.500   1.4101   0.04476   0.03788  -0.0307   0.0306   1.0000
  12.750   1.4116   0.04805   0.04130  -0.0290   0.0293   1.0000
  13.000   1.4115   0.05075   0.04428  -0.0279   0.0285   1.0000
  13.250   1.4101   0.05381   0.04758  -0.0271   0.0277   1.0000
  13.500   1.4067   0.05712   0.05111  -0.0266   0.0269   1.0000
  13.750   1.4024   0.06058   0.05477  -0.0265   0.0262   1.0000
  14.000   1.3965   0.06428   0.05865  -0.0268   0.0255   1.0000
  14.250   1.3906   0.06808   0.06260  -0.0275   0.0248   1.0000
  14.500   1.3845   0.07202   0.06666  -0.0283   0.0243   1.0000
  14.750   1.3780   0.07616   0.07090  -0.0292   0.0237   1.0000
  15.000   1.3669   0.08122   0.07611  -0.0304   0.0233   1.0000
  15.250   1.3509   0.08720   0.08230  -0.0323   0.0231   1.0000
  15.500   1.3332   0.09369   0.08900  -0.0350   0.0230   1.0000
  15.750   1.3148   0.10057   0.09609  -0.0384   0.0230   1.0000
  16.000   1.2965   0.10779   0.10352  -0.0423   0.0231   1.0000
  16.250   1.2776   0.11553   0.11146  -0.0470   0.0231   1.0000
  16.500   1.2577   0.12405   0.12019  -0.0525   0.0233   1.0000
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