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GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 494 AIRFOIL (goe494-il)
Reynolds number: 1,000,000
Max Cl/Cd: 164.34 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe494-il-1000000.txt
Download as CSV file: xf-goe494-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 494 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3638   0.10843   0.10678  -0.0285   1.0000   0.0082
  -9.250  -0.3608   0.10608   0.10444  -0.0282   1.0000   0.0083
  -9.000  -0.3594   0.10374   0.10213  -0.0278   1.0000   0.0084
  -8.750  -0.3588   0.10186   0.10027  -0.0268   1.0000   0.0087
  -8.500  -0.3557   0.09959   0.09801  -0.0269   0.9997   0.0090
  -8.250  -0.3404   0.09588   0.09431  -0.0307   0.9986   0.0092
  -8.000  -0.3243   0.09228   0.09070  -0.0347   0.9969   0.0097
  -7.750  -0.3072   0.08835   0.08677  -0.0393   0.9949   0.0106
  -7.500  -0.2896   0.08410   0.08253  -0.0462   0.9901   0.0115
  -7.250  -0.2680   0.07943   0.07785  -0.0529   0.9863   0.0116
  -7.000  -0.2435   0.07468   0.07309  -0.0599   0.9841   0.0116
  -6.750  -0.2233   0.06808   0.06649  -0.0685   0.9795   0.0119
  -6.500  -0.2014   0.06447   0.06287  -0.0733   0.9759   0.0123
  -6.250  -0.1760   0.06257   0.06095  -0.0767   0.9737   0.0133
  -6.000  -0.1417   0.05829   0.05666  -0.0852   0.9716   0.0147
  -5.750  -0.0914   0.05224   0.05054  -0.0991   0.9686   0.0164
  -5.500  -0.0453   0.02713   0.02545  -0.1013   0.9409   0.0152
  -5.250  -0.0164   0.02060   0.01879  -0.1111   0.9321   0.0148
  -5.000   0.0396   0.00587   0.00311  -0.1339   0.9298   0.0163
  -4.750   0.0777   0.01524   0.01183  -0.1444   0.9408   0.0179
  -4.500   0.1040   0.01535   0.01195  -0.1444   0.9345   0.0187
  -4.000   0.1598   0.01374   0.01000  -0.1449   0.9221   0.0219
  -3.250   0.2420   0.01130   0.00706  -0.1454   0.9000   0.0280
  -3.000   0.2692   0.01057   0.00618  -0.1453   0.8914   0.0295
  -2.750   0.2966   0.01016   0.00565  -0.1452   0.8831   0.0318
  -2.500   0.3241   0.00945   0.00478  -0.1450   0.8743   0.0322
  -2.250   0.3514   0.00879   0.00400  -0.1448   0.8642   0.0321
  -2.000   0.3786   0.00820   0.00330  -0.1446   0.8541   0.0317
  -1.750   0.4058   0.00776   0.00277  -0.1444   0.8440   0.0315
  -1.500   0.4330   0.00741   0.00236  -0.1442   0.8334   0.0317
  -1.250   0.4603   0.00705   0.00194  -0.1440   0.8226   0.0313
  -1.000   0.4876   0.00679   0.00161  -0.1438   0.8123   0.0315
  -0.750   0.5149   0.00662   0.00136  -0.1436   0.8029   0.0324
  -0.500   0.5422   0.00652   0.00122  -0.1434   0.7936   0.0336
  -0.250   0.5693   0.00647   0.00114  -0.1432   0.7839   0.0342
   0.000   0.5964   0.00639   0.00099  -0.1430   0.7739   0.0349
   0.250   0.6235   0.00635   0.00090  -0.1427   0.7649   0.0355
   0.500   0.6508   0.00633   0.00084  -0.1425   0.7568   0.0361
   0.750   0.6777   0.00634   0.00081  -0.1423   0.7474   0.0372
   1.000   0.7041   0.00639   0.00080  -0.1419   0.7341   0.0388
   1.250   0.7304   0.00645   0.00081  -0.1414   0.7168   0.0409
   1.500   0.7572   0.00626   0.00088  -0.1413   0.7056   0.1712
   1.750   0.7837   0.00599   0.00105  -0.1412   0.6922   0.3729
   2.000   0.8100   0.00574   0.00121  -0.1410   0.6780   0.5573
   2.250   0.8332   0.00507   0.00134  -0.1400   0.6515   1.0000
   2.500   0.8574   0.00534   0.00141  -0.1392   0.5965   1.0000
   2.750   0.8775   0.00607   0.00167  -0.1377   0.4968   1.0000
   3.000   0.8932   0.00742   0.00218  -0.1358   0.3144   1.0000
   3.250   0.9115   0.00857   0.00268  -0.1343   0.1785   1.0000
   3.500   0.9297   0.00979   0.00327  -0.1328   0.0436   1.0000
   3.750   0.9543   0.01018   0.00363  -0.1321   0.0289   1.0000
   4.000   0.9794   0.01052   0.00398  -0.1316   0.0222   1.0000
   4.250   1.0041   0.01090   0.00434  -0.1309   0.0180   1.0000
   4.500   1.0273   0.01150   0.00502  -0.1299   0.0153   1.0000
   4.750   1.0520   0.01185   0.00542  -0.1293   0.0143   1.0000
   5.000   1.0766   0.01222   0.00580  -0.1287   0.0128   1.0000
   5.250   1.1004   0.01268   0.00626  -0.1279   0.0113   1.0000
   5.500   1.1163   0.01430   0.00805  -0.1256   0.0100   1.0000
   5.750   1.1400   0.01476   0.00855  -0.1248   0.0097   1.0000
   6.000   1.1628   0.01537   0.00921  -0.1239   0.0093   1.0000
   6.250   1.1849   0.01610   0.01002  -0.1228   0.0087   1.0000
   6.500   1.2064   0.01699   0.01097  -0.1216   0.0081   1.0000
   6.750   1.2279   0.01794   0.01198  -0.1205   0.0076   1.0000
   7.000   1.2503   0.01860   0.01268  -0.1196   0.0071   1.0000
   7.250   1.2711   0.01967   0.01379  -0.1186   0.0066   1.0000
   7.500   1.2898   0.02244   0.01676  -0.1170   0.0064   1.0000
   7.750   1.3087   0.02640   0.02107  -0.1153   0.0062   1.0000
   8.000   1.3278   0.02836   0.02328  -0.1138   0.0061   1.0000
   8.250   1.3472   0.02996   0.02509  -0.1124   0.0058   1.0000
   8.500   1.3631   0.03306   0.02852  -0.1102   0.0056   1.0000
   8.750   1.3683   0.03946   0.03546  -0.1063   0.0054   1.0000
   9.000   1.3594   0.04650   0.04303  -0.1014   0.0058   1.0000
  10.500   1.3075   0.06761   0.06529  -0.0801   0.0065   1.0000
  10.750   1.2873   0.07170   0.06953  -0.0779   0.0065   1.0000
  11.000   1.2651   0.07654   0.07452  -0.0770   0.0065   1.0000
  11.250   1.2438   0.08199   0.08011  -0.0775   0.0065   1.0000
  11.500   1.2235   0.08816   0.08643  -0.0794   0.0065   1.0000
  11.750   1.2013   0.09566   0.09407  -0.0830   0.0066   1.0000
  12.000   1.1769   0.10538   0.10393  -0.0891   0.0067   1.0000
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