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GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il)
Reynolds number: 500,000
Max Cl/Cd: 107.06 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe336-il-500000.txt
Download as CSV file: xf-goe336-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 336 (MVA H.44) 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  -0.2932   0.09268   0.09057  -0.0280   1.0000   0.0225
  -8.000  -0.2934   0.08993   0.08786  -0.0289   1.0000   0.0236
  -7.750  -0.2955   0.08666   0.08464  -0.0350   0.9949   0.0242
  -7.500  -0.2695   0.08103   0.07897  -0.0456   0.9836   0.0244
  -7.250  -0.2541   0.07479   0.07271  -0.0508   0.9704   0.0248
  -7.000  -0.2352   0.07181   0.06971  -0.0520   0.9527   0.0253
  -6.750  -0.2166   0.06886   0.06668  -0.0542   0.9260   0.0258
  -6.500  -0.2020   0.06607   0.06377  -0.0559   0.8910   0.0265
  -6.250  -0.1870   0.06316   0.06070  -0.0578   0.8542   0.0274
  -6.000  -0.1675   0.05969   0.05701  -0.0612   0.8214   0.0294
  -5.750  -0.1339   0.05511   0.05212  -0.0680   0.7962   0.0307
  -5.500  -0.1247   0.04995   0.04680  -0.0691   0.7777   0.0315
  -5.250  -0.1069   0.04804   0.04477  -0.0692   0.7615   0.0321
  -5.000  -0.0868   0.04608   0.04268  -0.0697   0.7478   0.0329
  -4.750  -0.0647   0.04381   0.04027  -0.0706   0.7360   0.0342
  -4.500  -0.0285   0.04067   0.03679  -0.0731   0.7260   0.0384
  -4.250  -0.0126   0.03552   0.03145  -0.0738   0.7167   0.0397
  -4.000   0.0088   0.03418   0.03002  -0.0737   0.7069   0.0405
  -3.750   0.0316   0.03281   0.02852  -0.0736   0.6971   0.0418
  -3.500   0.0564   0.03097   0.02654  -0.0737   0.6873   0.0442
  -3.250   0.0826   0.02672   0.02182  -0.0735   0.6793   0.0494
  -3.000   0.1061   0.02590   0.02097  -0.0734   0.6687   0.0506
  -2.750   0.1307   0.02502   0.02000  -0.0731   0.6580   0.0527
  -2.500   0.1624   0.02494   0.01948  -0.0723   0.6475   0.0588
  -2.250   0.1787   0.01466   0.00805  -0.0698   0.6406   0.0402
  -2.000   0.2054   0.01369   0.00684  -0.0693   0.6293   0.0401
  -1.750   0.2322   0.01292   0.00586  -0.0689   0.6180   0.0401
  -1.500   0.2592   0.01227   0.00504  -0.0685   0.6063   0.0401
  -1.250   0.2861   0.01173   0.00439  -0.0681   0.5949   0.0404
  -1.000   0.3129   0.01132   0.00388  -0.0677   0.5845   0.0409
  -0.750   0.3395   0.01103   0.00350  -0.0674   0.5746   0.0416
  -0.500   0.3663   0.01078   0.00320  -0.0670   0.5652   0.0423
  -0.250   0.3929   0.01060   0.00296  -0.0667   0.5570   0.0432
   0.000   0.4198   0.01046   0.00279  -0.0664   0.5490   0.0447
   0.250   0.4464   0.01038   0.00264  -0.0660   0.5416   0.0464
   0.500   0.4734   0.01028   0.00250  -0.0657   0.5337   0.0478
   0.750   0.4999   0.01020   0.00238  -0.0654   0.5268   0.0522
   1.000   0.5270   0.01012   0.00237  -0.0651   0.5205   0.0652
   1.250   0.5540   0.01014   0.00243  -0.0649   0.5152   0.0962
   1.500   0.5812   0.01017   0.00247  -0.0647   0.5093   0.1117
   1.750   0.6082   0.01018   0.00250  -0.0646   0.5026   0.1242
   2.000   0.6349   0.01021   0.00253  -0.0644   0.4959   0.1391
   2.500   0.6869   0.01003   0.00267  -0.0638   0.4825   0.2833
   2.750   0.7841   0.00875   0.00296  -0.0796   0.4723   1.0000
   3.000   0.8095   0.00888   0.00301  -0.0791   0.4662   1.0000
   3.250   0.8352   0.00894   0.00307  -0.0786   0.4600   1.0000
   3.500   0.8605   0.00906   0.00314  -0.0781   0.4545   1.0000
   3.750   0.8860   0.00916   0.00323  -0.0777   0.4494   1.0000
   4.000   0.9115   0.00925   0.00332  -0.0772   0.4433   1.0000
   4.250   0.9364   0.00939   0.00341  -0.0766   0.4378   1.0000
   4.500   0.9619   0.00947   0.00351  -0.0762   0.4315   1.0000
   4.750   0.9867   0.00960   0.00361  -0.0756   0.4240   1.0000
   5.000   1.0118   0.00970   0.00374  -0.0751   0.4168   1.0000
   5.250   1.0361   0.00986   0.00385  -0.0744   0.4072   1.0000
   5.500   1.0604   0.00999   0.00396  -0.0738   0.3928   1.0000
   5.750   1.0844   0.01016   0.00411  -0.0731   0.3773   1.0000
   6.000   1.1081   0.01035   0.00426  -0.0724   0.3570   1.0000
   6.250   1.1283   0.01082   0.00450  -0.0712   0.3065   1.0000
   7.000   1.1783   0.01318   0.00612  -0.0660   0.1767   1.0000
   7.250   1.1949   0.01391   0.00664  -0.0643   0.1395   1.0000
   7.500   1.2113   0.01462   0.00718  -0.0626   0.1144   1.0000
   7.750   1.2276   0.01529   0.00773  -0.0608   0.0931   1.0000
   8.000   1.2389   0.01627   0.00848  -0.0583   0.0601   1.0000
   8.250   1.2559   0.01682   0.00901  -0.0566   0.0535   1.0000
   8.500   1.2731   0.01733   0.00952  -0.0549   0.0477   1.0000
   8.750   1.2908   0.01778   0.00998  -0.0534   0.0418   1.0000
   9.000   1.3054   0.01842   0.01055  -0.0514   0.0248   1.0000
   9.250   1.3128   0.01945   0.01152  -0.0483   0.0180   1.0000
   9.500   1.3245   0.02010   0.01224  -0.0458   0.0164   1.0000
   9.750   1.3346   0.02077   0.01298  -0.0431   0.0158   1.0000
  10.000   1.3441   0.02154   0.01385  -0.0404   0.0153   1.0000
  10.250   1.3527   0.02245   0.01486  -0.0379   0.0148   1.0000
  10.500   1.3601   0.02353   0.01605  -0.0355   0.0144   1.0000
  10.750   1.3660   0.02480   0.01743  -0.0333   0.0140   1.0000
  11.000   1.3702   0.02632   0.01906  -0.0312   0.0136   1.0000
  11.250   1.3717   0.02820   0.02105  -0.0292   0.0133   1.0000
  11.500   1.3694   0.03061   0.02357  -0.0275   0.0129   1.0000
  11.750   1.3632   0.03363   0.02671  -0.0262   0.0126   1.0000
  12.000   1.3689   0.03563   0.02879  -0.0256   0.0124   1.0000
  12.250   1.3716   0.03799   0.03125  -0.0250   0.0122   1.0000
  12.500   1.3720   0.04063   0.03400  -0.0245   0.0120   1.0000
  12.750   1.3711   0.04347   0.03694  -0.0241   0.0119   1.0000
  13.000   1.3692   0.04645   0.04001  -0.0237   0.0117   1.0000
  13.250   1.3666   0.04955   0.04320  -0.0234   0.0116   1.0000
  13.500   1.3635   0.05274   0.04648  -0.0232   0.0114   1.0000
  13.750   1.3601   0.05599   0.04982  -0.0231   0.0113   1.0000
  14.000   1.3571   0.05927   0.05318  -0.0230   0.0112   1.0000
  14.250   1.3543   0.06257   0.05656  -0.0230   0.0111   1.0000
  14.500   1.3519   0.06584   0.05990  -0.0230   0.0110   1.0000
  14.750   1.3501   0.06906   0.06320  -0.0230   0.0109   1.0000
  15.000   1.3488   0.07223   0.06644  -0.0230   0.0107   1.0000
  15.250   1.3483   0.07526   0.06953  -0.0229   0.0106   1.0000
  15.500   1.3486   0.07820   0.07253  -0.0228   0.0105   1.0000
  15.750   1.3496   0.08100   0.07539  -0.0227   0.0104   1.0000
  16.000   1.3515   0.08368   0.07813  -0.0224   0.0103   1.0000
  16.250   1.3544   0.08611   0.08060  -0.0220   0.0102   1.0000
  16.500   1.3612   0.08761   0.08209  -0.0206   0.0100   1.0000
  16.750   1.4012   0.08347   0.07779  -0.0126   0.0096   1.0000
  17.000   1.3859   0.08893   0.08345  -0.0153   0.0095   1.0000
  17.250   1.3817   0.09286   0.08753  -0.0164   0.0095   1.0000
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