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GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 758 AIRFOIL (goe758-il)
Reynolds number: 500,000
Max Cl/Cd: 102.78 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe758-il-500000-n5.txt
Download as CSV file: xf-goe758-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 758 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3974   0.04018   0.03697  -0.1176   0.8707   0.0209
 -10.250  -0.4166   0.03752   0.03407  -0.1157   0.8518   0.0210
 -10.000  -0.4187   0.03547   0.03182  -0.1144   0.8374   0.0211
  -9.750  -0.4142   0.03373   0.02989  -0.1133   0.8243   0.0213
  -9.500  -0.4064   0.03210   0.02806  -0.1121   0.8116   0.0214
  -9.250  -0.3969   0.03045   0.02620  -0.1110   0.7987   0.0216
  -9.000  -0.3854   0.02882   0.02433  -0.1098   0.7849   0.0219
  -8.750  -0.3723   0.02723   0.02249  -0.1087   0.7695   0.0222
  -8.500  -0.3571   0.02587   0.02088  -0.1076   0.7512   0.0226
  -8.250  -0.3412   0.02450   0.01920  -0.1064   0.7301   0.0230
  -8.000  -0.3242   0.02323   0.01760  -0.1051   0.7069   0.0234
  -7.250  -0.2646   0.02021   0.01371  -0.1021   0.6590   0.0243
  -7.000  -0.2419   0.01954   0.01281  -0.1014   0.6497   0.0245
  -6.750  -0.2184   0.01899   0.01205  -0.1007   0.6417   0.0246
  -6.500  -0.1960   0.01773   0.01069  -0.1002   0.6355   0.0251
  -6.250  -0.1718   0.01707   0.00995  -0.0997   0.6293   0.0255
  -5.750  -0.1221   0.01597   0.00867  -0.0988   0.6192   0.0260
  -5.500  -0.0967   0.01546   0.00808  -0.0984   0.6145   0.0262
  -5.250  -0.0714   0.01501   0.00755  -0.0980   0.6100   0.0265
  -5.000  -0.0459   0.01460   0.00705  -0.0976   0.6059   0.0268
  -4.750  -0.0200   0.01417   0.00658  -0.0972   0.6021   0.0270
  -4.500   0.0060   0.01379   0.00615  -0.0969   0.5981   0.0273
  -4.250   0.0318   0.01344   0.00575  -0.0965   0.5941   0.0276
  -4.000   0.0575   0.01313   0.00537  -0.0960   0.5904   0.0279
  -3.750   0.0839   0.01284   0.00506  -0.0957   0.5869   0.0283
  -3.500   0.1103   0.01258   0.00476  -0.0954   0.5830   0.0287
  -3.250   0.1367   0.01235   0.00449  -0.0951   0.5791   0.0291
  -3.000   0.1628   0.01213   0.00422  -0.0948   0.5751   0.0293
  -2.750   0.1892   0.01192   0.00398  -0.0944   0.5712   0.0295
  -2.500   0.2152   0.01160   0.00365  -0.0941   0.5669   0.0299
  -2.250   0.2414   0.01136   0.00339  -0.0938   0.5624   0.0304
  -2.000   0.2677   0.01119   0.00318  -0.0934   0.5583   0.0309
  -1.750   0.2946   0.01103   0.00301  -0.0932   0.5546   0.0315
  -1.500   0.3217   0.01090   0.00287  -0.0930   0.5505   0.0321
  -1.250   0.3487   0.01080   0.00274  -0.0928   0.5462   0.0328
  -1.000   0.3755   0.01073   0.00263  -0.0926   0.5422   0.0336
  -0.750   0.4027   0.01066   0.00254  -0.0924   0.5385   0.0347
  -0.500   0.4300   0.01058   0.00246  -0.0922   0.5342   0.0360
  -0.250   0.4570   0.01052   0.00238  -0.0920   0.5296   0.0379
   0.000   0.4837   0.01049   0.00232  -0.0917   0.5253   0.0404
   0.250   0.5103   0.01029   0.00228  -0.0915   0.5210   0.0870
   0.500   0.5348   0.00983   0.00226  -0.0911   0.5163   0.2362
   0.750   0.5599   0.00959   0.00227  -0.0907   0.5113   0.3298
   1.000   0.5847   0.00934   0.00231  -0.0903   0.5065   0.4348
   1.250   0.6090   0.00909   0.00241  -0.0897   0.5013   0.5504
   1.500   0.6340   0.00901   0.00247  -0.0891   0.4960   0.6096
   1.750   0.6590   0.00894   0.00252  -0.0885   0.4906   0.6575
   2.000   0.6823   0.00878   0.00259  -0.0875   0.4845   0.7282
   2.500   0.7867   0.00854   0.00282  -0.0980   0.4702   1.0000
   2.750   0.8106   0.00867   0.00288  -0.0972   0.4633   1.0000
   3.000   0.8354   0.00877   0.00296  -0.0966   0.4565   1.0000
   3.250   0.8596   0.00890   0.00305  -0.0959   0.4496   1.0000
   3.500   0.8839   0.00903   0.00314  -0.0952   0.4431   1.0000
   3.750   0.9081   0.00917   0.00325  -0.0945   0.4354   1.0000
   4.000   0.9321   0.00933   0.00336  -0.0938   0.4279   1.0000
   4.250   0.9562   0.00948   0.00348  -0.0931   0.4202   1.0000
   4.500   0.9800   0.00965   0.00363  -0.0924   0.4126   1.0000
   4.750   1.0032   0.00985   0.00378  -0.0915   0.4026   1.0000
   5.000   1.0265   0.01004   0.00393  -0.0907   0.3925   1.0000
   5.250   1.0492   0.01026   0.00412  -0.0899   0.3840   1.0000
   5.500   1.0730   0.01044   0.00429  -0.0892   0.3769   1.0000
   5.750   1.0953   0.01068   0.00449  -0.0883   0.3693   1.0000
   6.000   1.1184   0.01089   0.00469  -0.0875   0.3608   1.0000
   6.250   1.1402   0.01114   0.00492  -0.0865   0.3528   1.0000
   6.500   1.1629   0.01136   0.00513  -0.0856   0.3454   1.0000
   6.750   1.1844   0.01162   0.00538  -0.0846   0.3394   1.0000
   7.000   1.2068   0.01184   0.00562  -0.0837   0.3330   1.0000
   7.250   1.2269   0.01215   0.00590  -0.0825   0.3245   1.0000
   7.500   1.2473   0.01243   0.00617  -0.0813   0.3149   1.0000
   7.750   1.2658   0.01277   0.00649  -0.0798   0.3054   1.0000
   8.000   1.2847   0.01309   0.00680  -0.0784   0.2962   1.0000
   8.250   1.3017   0.01340   0.00712  -0.0766   0.2887   1.0000
   8.500   1.3168   0.01377   0.00747  -0.0745   0.2789   1.0000
   8.750   1.3322   0.01415   0.00783  -0.0725   0.2687   1.0000
   9.000   1.3461   0.01459   0.00827  -0.0703   0.2580   1.0000
   9.250   1.3587   0.01511   0.00875  -0.0680   0.2456   1.0000
   9.500   1.3704   0.01570   0.00930  -0.0657   0.2321   1.0000
   9.750   1.3796   0.01642   0.00996  -0.0632   0.2142   1.0000
  10.000   1.3827   0.01749   0.01090  -0.0600   0.1900   1.0000
  10.250   1.3870   0.01857   0.01190  -0.0572   0.1686   1.0000
  10.500   1.3743   0.02072   0.01380  -0.0529   0.1253   1.0000
  10.750   1.3620   0.02311   0.01598  -0.0492   0.0920   1.0000
  11.000   1.3635   0.02477   0.01762  -0.0471   0.0805   1.0000
  11.250   1.3673   0.02637   0.01923  -0.0454   0.0723   1.0000
  11.500   1.3694   0.02818   0.02104  -0.0438   0.0617   1.0000
  11.750   1.3583   0.03120   0.02393  -0.0418   0.0370   1.0000
  12.000   1.3514   0.03408   0.02678  -0.0403   0.0249   1.0000
  12.250   1.3515   0.03648   0.02921  -0.0394   0.0209   1.0000
  12.500   1.3541   0.03871   0.03150  -0.0388   0.0191   1.0000
  12.750   1.3558   0.04109   0.03394  -0.0382   0.0177   1.0000
  13.000   1.3585   0.04344   0.03636  -0.0377   0.0168   1.0000
  13.250   1.3606   0.04587   0.03887  -0.0373   0.0160   1.0000
  13.500   1.3619   0.04843   0.04152  -0.0370   0.0154   1.0000
  13.750   1.3620   0.05117   0.04433  -0.0367   0.0147   1.0000
  14.000   1.3595   0.05426   0.04749  -0.0365   0.0140   1.0000
  14.250   1.3584   0.05723   0.05054  -0.0364   0.0136   1.0000
  14.500   1.3586   0.06011   0.05350  -0.0363   0.0131   1.0000
  14.750   1.3583   0.06310   0.05659  -0.0364   0.0128   1.0000
  15.000   1.3566   0.06633   0.05990  -0.0365   0.0125   1.0000
  15.250   1.3544   0.06967   0.06334  -0.0368   0.0122   1.0000
  15.500   1.3516   0.07318   0.06693  -0.0371   0.0119   1.0000
  15.750   1.3487   0.07676   0.07059  -0.0376   0.0116   1.0000
  16.000   1.3444   0.08056   0.07447  -0.0381   0.0113   1.0000
  16.250   1.3391   0.08459   0.07858  -0.0388   0.0111   1.0000
  16.500   1.3324   0.08889   0.08298  -0.0397   0.0109   1.0000
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