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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 500,000
Max Cl/Cd: 107.43 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe180-il-500000.txt
Download as CSV file: xf-goe180-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3642   0.09335   0.09111  -0.0298   1.0000   0.0218
  -8.250  -0.3675   0.09039   0.08818  -0.0300   1.0000   0.0218
  -8.000  -0.3755   0.08660   0.08444  -0.0286   1.0000   0.0221
  -7.750  -0.3748   0.08465   0.08252  -0.0267   1.0000   0.0224
  -7.500  -0.3727   0.08272   0.08063  -0.0254   1.0000   0.0227
  -7.250  -0.3751   0.08067   0.07863  -0.0245   1.0000   0.0230
  -7.000  -0.3698   0.07788   0.07585  -0.0262   0.9990   0.0234
  -6.750  -0.3424   0.07293   0.07088  -0.0345   0.9957   0.0245
  -6.250  -0.2135   0.03917   0.03706  -0.0664   0.9750   0.0283
  -6.000  -0.2377   0.05006   0.04768  -0.0699   0.9814   0.0283
  -5.750  -0.2104   0.04799   0.04557  -0.0725   0.9768   0.0293
  -5.500  -0.1754   0.04401   0.04147  -0.0781   0.9735   0.0313
  -5.250  -0.1360   0.03304   0.02989  -0.0871   0.9662   0.0354
  -5.000  -0.1055   0.03158   0.02842  -0.0892   0.9620   0.0364
  -4.750  -0.0743   0.02996   0.02672  -0.0912   0.9567   0.0384
  -4.500  -0.0409   0.02502   0.02122  -0.0940   0.9490   0.0450
  -4.250  -0.0092   0.02383   0.02001  -0.0956   0.9417   0.0466
  -4.000   0.0259   0.02193   0.01760  -0.0973   0.9331   0.0547
  -3.750   0.0556   0.02028   0.01598  -0.0985   0.9226   0.0568
  -3.500   0.0889   0.01496   0.00975  -0.0986   0.9125   0.0414
  -3.250   0.1185   0.01310   0.00756  -0.0987   0.9006   0.0395
  -3.000   0.1467   0.01217   0.00641  -0.0984   0.8871   0.0395
  -2.750   0.1739   0.01149   0.00559  -0.0980   0.8721   0.0401
  -2.500   0.2006   0.01085   0.00480  -0.0974   0.8546   0.0401
  -2.250   0.2271   0.01035   0.00418  -0.0968   0.8334   0.0405
  -2.000   0.2534   0.00996   0.00366  -0.0962   0.8078   0.0409
  -1.750   0.2792   0.00967   0.00321  -0.0954   0.7747   0.0413
  -1.500   0.3045   0.00953   0.00287  -0.0946   0.7353   0.0421
  -1.250   0.3299   0.00948   0.00261  -0.0939   0.6953   0.0430
  -1.000   0.3556   0.00939   0.00233  -0.0933   0.6613   0.0437
  -0.750   0.3818   0.00930   0.00207  -0.0928   0.6324   0.0454
  -0.500   0.4084   0.00929   0.00194  -0.0924   0.6084   0.0479
  -0.250   0.4352   0.00931   0.00186  -0.0921   0.5882   0.0511
   0.000   0.4622   0.00931   0.00182  -0.0918   0.5719   0.0614
   0.250   0.4894   0.00918   0.00183  -0.0917   0.5589   0.1255
   0.500   0.5163   0.00885   0.00190  -0.0918   0.5475   0.2848
   0.750   0.5403   0.00723   0.00203  -0.0910   0.5368   1.0000
   1.000   0.5674   0.00737   0.00205  -0.0908   0.5257   1.0000
   1.250   0.5949   0.00748   0.00208  -0.0906   0.5160   1.0000
   1.500   0.6220   0.00763   0.00213  -0.0904   0.5070   1.0000
   1.750   0.6495   0.00774   0.00217  -0.0902   0.4983   1.0000
   2.000   0.6767   0.00788   0.00223  -0.0900   0.4903   1.0000
   2.250   0.7042   0.00799   0.00231  -0.0899   0.4828   1.0000
   2.500   0.7315   0.00814   0.00239  -0.0897   0.4764   1.0000
   2.750   0.7590   0.00824   0.00247  -0.0896   0.4689   1.0000
   3.000   0.7860   0.00840   0.00256  -0.0894   0.4621   1.0000
   3.250   0.8136   0.00849   0.00267  -0.0893   0.4550   1.0000
   3.750   0.8680   0.00875   0.00289  -0.0890   0.4403   1.0000
   4.000   0.8947   0.00892   0.00301  -0.0887   0.4323   1.0000
   4.250   0.9221   0.00902   0.00313  -0.0886   0.4233   1.0000
   4.500   0.9489   0.00917   0.00327  -0.0884   0.4143   1.0000
   4.750   0.9756   0.00932   0.00340  -0.0882   0.4039   1.0000
   5.000   1.0025   0.00946   0.00356  -0.0880   0.3924   1.0000
   5.250   1.0290   0.00962   0.00372  -0.0877   0.3788   1.0000
   5.500   1.0550   0.00982   0.00388  -0.0874   0.3612   1.0000
   5.750   1.0806   0.01007   0.00408  -0.0870   0.3373   1.0000
   6.000   1.1046   0.01049   0.00433  -0.0865   0.3013   1.0000
   6.250   1.1275   0.01103   0.00469  -0.0858   0.2684   1.0000
   6.500   1.1507   0.01155   0.00508  -0.0851   0.2459   1.0000
   7.000   1.1985   0.01240   0.00584  -0.0840   0.2160   1.0000
   7.250   1.2228   0.01277   0.00619  -0.0835   0.2028   1.0000
   7.500   1.2470   0.01314   0.00654  -0.0830   0.1883   1.0000
   7.750   1.2708   0.01354   0.00691  -0.0824   0.1716   1.0000
   8.000   1.2934   0.01406   0.00731  -0.0817   0.1466   1.0000
   8.250   1.3141   0.01474   0.00785  -0.0808   0.1240   1.0000
   8.500   1.3333   0.01556   0.00854  -0.0796   0.0974   1.0000
   8.750   1.3408   0.01751   0.01002  -0.0768   0.0336   1.0000
   9.000   1.3586   0.01840   0.01095  -0.0752   0.0271   1.0000
   9.250   1.3740   0.01948   0.01207  -0.0734   0.0234   1.0000
   9.500   1.3929   0.02014   0.01282  -0.0721   0.0218   1.0000
   9.750   1.4096   0.02095   0.01369  -0.0705   0.0202   1.0000
  10.000   1.4225   0.02200   0.01483  -0.0684   0.0189   1.0000
  10.250   1.4282   0.02346   0.01640  -0.0652   0.0179   1.0000
  10.500   1.4387   0.02434   0.01737  -0.0627   0.0174   1.0000
  10.750   1.4470   0.02538   0.01852  -0.0600   0.0168   1.0000
  11.000   1.4541   0.02654   0.01977  -0.0574   0.0161   1.0000
  11.250   1.4602   0.02781   0.02113  -0.0549   0.0155   1.0000
  11.500   1.4649   0.02927   0.02267  -0.0526   0.0150   1.0000
  11.750   1.4652   0.03117   0.02466  -0.0502   0.0145   1.0000
  12.000   1.4590   0.03381   0.02740  -0.0478   0.0141   1.0000
  12.250   1.4499   0.03696   0.03068  -0.0456   0.0138   1.0000
  12.500   1.4542   0.03902   0.03286  -0.0446   0.0136   1.0000
  12.750   1.4564   0.04140   0.03536  -0.0437   0.0133   1.0000
  13.000   1.4572   0.04403   0.03811  -0.0431   0.0131   1.0000
  13.250   1.4570   0.04689   0.04109  -0.0426   0.0128   1.0000
  13.500   1.4562   0.04990   0.04422  -0.0423   0.0126   1.0000
  13.750   1.4548   0.05306   0.04750  -0.0421   0.0124   1.0000
  14.000   1.4531   0.05632   0.05087  -0.0421   0.0122   1.0000
  14.250   1.4507   0.05970   0.05435  -0.0422   0.0120   1.0000
  14.500   1.4479   0.06318   0.05795  -0.0425   0.0118   1.0000
  14.750   1.4449   0.06680   0.06167  -0.0429   0.0116   1.0000
  15.000   1.4414   0.07051   0.06548  -0.0435   0.0114   1.0000
  15.250   1.4376   0.07432   0.06938  -0.0442   0.0112   1.0000
  15.500   1.4334   0.07820   0.07334  -0.0448   0.0110   1.0000
  15.750   1.4286   0.08211   0.07733  -0.0453   0.0108   1.0000
  16.000   1.4217   0.08606   0.08137  -0.0451   0.0106   1.0000
  16.250   1.4111   0.09086   0.08633  -0.0454   0.0104   1.0000
  16.500   1.4027   0.09599   0.09161  -0.0475   0.0103   1.0000
  16.750   1.3938   0.10121   0.09699  -0.0496   0.0103   1.0000
  17.000   1.3839   0.10674   0.10268  -0.0520   0.0102   1.0000
  17.250   1.3736   0.11249   0.10860  -0.0546   0.0102   1.0000
  17.500   1.3624   0.11858   0.11484  -0.0575   0.0101   1.0000
  17.750   1.3506   0.12494   0.12136  -0.0608   0.0101   1.0000
  18.000   1.3383   0.13159   0.12818  -0.0643   0.0101   1.0000
  18.250   1.3255   0.13856   0.13530  -0.0683   0.0101   1.0000
  18.500   1.3124   0.14590   0.14279  -0.0727   0.0101   1.0000
  18.750   1.2985   0.15370   0.15075  -0.0775   0.0101   1.0000
  19.000   1.2840   0.16197   0.15917  -0.0829   0.0101   1.0000
  19.250   1.2689   0.17071   0.16805  -0.0886   0.0102   1.0000
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