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GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 368 AIRFOIL (goe368-il)
Reynolds number: 500,000
Max Cl/Cd: 83.91 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe368-il-500000.txt
Download as CSV file: xf-goe368-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 368 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3392   0.09462   0.09257  -0.0070   1.0000   0.0158
  -9.000  -0.4283   0.09955   0.09737  -0.0057   1.0000   0.0146
  -8.750  -0.4239   0.09652   0.09435  -0.0059   1.0000   0.0151
  -8.500  -0.4186   0.09361   0.09146  -0.0067   1.0000   0.0154
  -8.250  -0.4131   0.09090   0.08877  -0.0073   1.0000   0.0158
  -8.000  -0.4091   0.08795   0.08584  -0.0082   1.0000   0.0161
  -7.750  -0.4067   0.08488   0.08280  -0.0093   1.0000   0.0163
  -7.500  -0.4060   0.08196   0.07992  -0.0101   1.0000   0.0167
  -7.250  -0.4065   0.07897   0.07697  -0.0111   1.0000   0.0171
  -7.000  -0.4016   0.07539   0.07341  -0.0138   1.0000   0.0175
  -6.750  -0.3950   0.07148   0.06952  -0.0170   1.0000   0.0180
  -6.500  -0.3863   0.06724   0.06528  -0.0207   1.0000   0.0186
  -6.250  -0.3747   0.06258   0.06061  -0.0248   1.0000   0.0195
  -6.000  -0.3584   0.05748   0.05547  -0.0293   1.0000   0.0205
  -5.750  -0.3366   0.05205   0.04997  -0.0339   1.0000   0.0213
  -5.500  -0.3177   0.04349   0.04121  -0.0396   1.0000   0.0215
  -5.250  -0.3106   0.02950   0.02652  -0.0460   1.0000   0.0229
  -5.000  -0.2930   0.02683   0.02376  -0.0456   1.0000   0.0240
  -4.750  -0.2648   0.02408   0.02079  -0.0472   0.9981   0.0256
  -4.500  -0.2244   0.01732   0.01287  -0.0497   0.9929   0.0170
  -4.250  -0.1859   0.01464   0.00965  -0.0514   0.9864   0.0158
  -4.000  -0.1483   0.01349   0.00838  -0.0535   0.9780   0.0172
  -3.750  -0.1097   0.01236   0.00710  -0.0555   0.9672   0.0181
  -3.500  -0.0722   0.01115   0.00573  -0.0571   0.9486   0.0184
  -3.250  -0.0310   0.01024   0.00467  -0.0594   0.9148   0.0196
  -3.000   0.0030   0.00977   0.00393  -0.0601   0.8617   0.0210
  -2.750   0.0287   0.00929   0.00317  -0.0591   0.8224   0.0239
  -2.500   0.0542   0.00904   0.00269  -0.0582   0.7903   0.0279
  -2.250   0.0799   0.00883   0.00226  -0.0573   0.7566   0.0358
  -2.000   0.1049   0.00854   0.00217  -0.0566   0.7196   0.1273
  -1.750   0.1312   0.00871   0.00218  -0.0560   0.6870   0.1385
  -1.500   0.1579   0.00887   0.00217  -0.0555   0.6617   0.1451
  -1.250   0.1846   0.00896   0.00219  -0.0551   0.6415   0.1531
  -1.000   0.2118   0.00912   0.00221  -0.0547   0.6230   0.1591
  -0.750   0.2385   0.00905   0.00207  -0.0543   0.6053   0.1631
  -0.500   0.2653   0.00904   0.00200  -0.0539   0.5863   0.1665
  -0.250   0.2923   0.00904   0.00192  -0.0536   0.5641   0.1704
   0.000   0.3192   0.00905   0.00182  -0.0532   0.5379   0.1745
   0.250   0.3458   0.00905   0.00174  -0.0528   0.5056   0.1802
   0.500   0.3722   0.00916   0.00170  -0.0524   0.4720   0.1867
   0.750   0.3985   0.00924   0.00169  -0.0520   0.4451   0.1940
   1.000   0.4253   0.00937   0.00171  -0.0516   0.4238   0.2018
   1.250   0.4519   0.00943   0.00173  -0.0513   0.4065   0.2107
   1.500   0.4787   0.00951   0.00177  -0.0510   0.3910   0.2196
   1.750   0.5056   0.00960   0.00182  -0.0508   0.3764   0.2291
   2.250   0.5593   0.00971   0.00193  -0.0502   0.3468   0.2527
   2.750   0.6122   0.00964   0.00213  -0.0498   0.3162   0.3670
   3.000   0.6441   0.00839   0.00226  -0.0507   0.2994   1.0000
   3.250   0.6704   0.00860   0.00237  -0.0503   0.2834   1.0000
   3.500   0.6966   0.00882   0.00251  -0.0499   0.2678   1.0000
   3.750   0.7227   0.00906   0.00268  -0.0495   0.2537   1.0000
   4.000   0.7487   0.00930   0.00284  -0.0492   0.2400   1.0000
   4.250   0.7745   0.00957   0.00300  -0.0488   0.2234   1.0000
   4.500   0.8007   0.00979   0.00318  -0.0484   0.2128   1.0000
   4.750   0.8268   0.01002   0.00339  -0.0481   0.2035   1.0000
   5.000   0.8528   0.01027   0.00358  -0.0477   0.1918   1.0000
   5.250   0.8786   0.01052   0.00378  -0.0474   0.1794   1.0000
   5.500   0.9045   0.01078   0.00398  -0.0470   0.1644   1.0000
   5.750   0.9292   0.01122   0.00424  -0.0466   0.1317   1.0000
   6.000   0.9459   0.01300   0.00537  -0.0452   0.0198   1.0000
   6.250   0.9712   0.01339   0.00585  -0.0446   0.0175   1.0000
   6.500   0.9960   0.01386   0.00645  -0.0440   0.0162   1.0000
   6.750   1.0201   0.01445   0.00717  -0.0433   0.0151   1.0000
   7.000   1.0425   0.01531   0.00820  -0.0424   0.0134   1.0000
   7.250   1.0632   0.01641   0.00947  -0.0413   0.0126   1.0000
   7.500   1.0811   0.01783   0.01105  -0.0399   0.0122   1.0000
   7.750   1.1015   0.01878   0.01210  -0.0388   0.0118   1.0000
   8.000   1.1203   0.01989   0.01332  -0.0375   0.0116   1.0000
   8.250   1.1369   0.02122   0.01476  -0.0360   0.0115   1.0000
   8.500   1.1505   0.02294   0.01656  -0.0341   0.0117   1.0000
   8.750   1.1628   0.02510   0.01876  -0.0321   0.0123   1.0000
   9.000   1.1794   0.02689   0.02059  -0.0307   0.0123   1.0000
   9.250   1.1979   0.02841   0.02217  -0.0295   0.0124   1.0000
   9.500   1.2179   0.02879   0.02267  -0.0283   0.0129   1.0000
   9.750   1.1978   0.02006   0.01459  -0.0237   0.0173   1.0000
  10.000   1.2112   0.02235   0.01702  -0.0221   0.0170   1.0000
  10.250   1.2209   0.02452   0.01935  -0.0204   0.0160   1.0000
  10.500   1.2275   0.02693   0.02189  -0.0185   0.0153   1.0000
  10.750   1.2295   0.02939   0.02448  -0.0161   0.0147   1.0000
  11.000   1.2308   0.03217   0.02735  -0.0140   0.0142   1.0000
  11.250   1.2343   0.03534   0.03063  -0.0125   0.0137   1.0000
  11.500   1.2300   0.03870   0.03412  -0.0108   0.0134   1.0000
  11.750   1.2226   0.04257   0.03814  -0.0095   0.0131   1.0000
  14.250   1.0425   0.10072   0.09787  -0.0291   0.0126   1.0000
  14.500   1.0238   0.10673   0.10403  -0.0339   0.0129   1.0000
  14.750   0.9976   0.11339   0.11088  -0.0394   0.0133   1.0000
  15.000   0.9735   0.12070   0.11834  -0.0449   0.0133   1.0000
  15.250   0.9416   0.13059   0.12841  -0.0527   0.0137   1.0000
  15.500   0.9016   0.14362   0.14168  -0.0625   0.0147   1.0000
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