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GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 398 AIRFOIL (goe398-il)
Reynolds number: 50,000
Max Cl/Cd: 10.6 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe398-il-50000.txt
Download as CSV file: xf-goe398-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 398 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2721   0.11564   0.10888  -0.0306   1.0000   0.2377
  -9.250  -0.2821   0.11458   0.10793  -0.0288   1.0000   0.2448
  -9.000  -0.3231   0.11662   0.11019  -0.0266   1.0000   0.2483
  -8.750  -0.2981   0.11104   0.10461  -0.0245   1.0000   0.2538
  -8.500  -0.3035   0.10958   0.10324  -0.0218   1.0000   0.2609
  -8.250  -0.3415   0.11087   0.10471  -0.0189   1.0000   0.2659
  -8.000  -0.3322   0.10716   0.10105  -0.0166   1.0000   0.2716
  -7.750  -0.3389   0.10584   0.09981  -0.0138   1.0000   0.2802
  -7.500  -0.3816   0.10705   0.10120  -0.0105   1.0000   0.2843
  -7.250  -0.3599   0.10280   0.09695  -0.0085   1.0000   0.2938
  -7.000  -0.3907   0.10292   0.09720  -0.0051   1.0000   0.3011
  -6.750  -0.4410   0.10397   0.09844  -0.0013   1.0000   0.3031
  -6.500  -0.4100   0.09950   0.09395   0.0006   1.0000   0.3177
  -6.250  -0.4684   0.10064   0.09526   0.0031   1.0000   0.3216
  -6.000  -0.4363   0.09630   0.09091   0.0067   1.0000   0.3345
  -5.750  -0.4567   0.09461   0.08932   0.0090   1.0000   0.3437
  -5.500  -0.4846   0.09408   0.08887   0.0103   1.0000   0.3580
  -5.250  -0.4643   0.09044   0.08526   0.0142   1.0000   0.3679
  -5.000  -0.4755   0.08842   0.08332   0.0165   1.0000   0.3824
  -4.750  -0.4836   0.08645   0.08141   0.0191   1.0000   0.3998
  -4.500  -0.4848   0.08437   0.07938   0.0224   1.0000   0.4199
  -4.250  -0.4854   0.08250   0.07756   0.0261   1.0000   0.4437
  -4.000  -0.4480   0.05894   0.05212  -0.0224   1.0000   0.1960
  -3.750  -0.4276   0.05362   0.04601  -0.0247   1.0000   0.1776
  -3.500  -0.4126   0.05107   0.04331  -0.0242   1.0000   0.1750
  -3.250  -0.3658   0.04818   0.03976  -0.0295   0.9877   0.1753
  -3.000  -0.3242   0.04600   0.03689  -0.0331   0.9759   0.1765
  -2.750  -0.2860   0.04437   0.03505  -0.0359   0.9637   0.1807
  -2.500  -0.2483   0.04344   0.03383  -0.0382   0.9515   0.1890
  -2.250  -0.2079   0.04237   0.03231  -0.0408   0.9395   0.1978
  -2.000  -0.1687   0.04185   0.03144  -0.0430   0.9269   0.2125
  -1.750  -0.1375   0.04119   0.03070  -0.0441   0.9139   0.2295
  -1.500  -0.1031   0.04060   0.03017  -0.0457   0.9011   0.2540
  -1.250  -0.0620   0.04020   0.02985  -0.0480   0.8885   0.2944
  -1.000  -0.0139   0.03973   0.02968  -0.0515   0.8763   0.3698
  -0.750   0.0834   0.03705   0.02944  -0.0632   0.8641   1.0000
  -0.500   0.1176   0.03786   0.02962  -0.0649   0.8502   1.0000
  -0.250   0.1576   0.03868   0.03001  -0.0673   0.8377   1.0000
   0.000   0.1874   0.03944   0.03046  -0.0682   0.8243   1.0000
   0.250   0.2066   0.04029   0.03109  -0.0675   0.8103   1.0000
   0.500   0.2323   0.04117   0.03175  -0.0677   0.7975   1.0000
   0.750   0.2776   0.04184   0.03217  -0.0704   0.7870   1.0000
   1.000   0.2869   0.04286   0.03306  -0.0684   0.7731   1.0000
   1.250   0.3048   0.04390   0.03396  -0.0677   0.7608   1.0000
   1.500   0.3527   0.04440   0.03427  -0.0703   0.7514   1.0000
   1.750   0.3550   0.04572   0.03550  -0.0677   0.7380   1.0000
   2.000   0.3711   0.04689   0.03657  -0.0668   0.7266   1.0000
   2.250   0.4153   0.04730   0.03684  -0.0686   0.7169   1.0000
   2.500   0.4135   0.04897   0.03846  -0.0659   0.7045   1.0000
   2.750   0.4345   0.05005   0.03945  -0.0654   0.6935   1.0000
   3.000   0.4683   0.05066   0.03998  -0.0661   0.6832   1.0000
   3.250   0.4694   0.05245   0.04172  -0.0638   0.6711   1.0000
   3.500   0.4977   0.05326   0.04247  -0.0639   0.6606   1.0000
   3.750   0.5192   0.05429   0.04345  -0.0634   0.6495   1.0000
   4.000   0.5233   0.05610   0.04524  -0.0616   0.6374   1.0000
   4.250   0.5630   0.05637   0.04546  -0.0622   0.6278   1.0000
   4.500   0.5688   0.05814   0.04721  -0.0606   0.6155   1.0000
   4.750   0.5730   0.06014   0.04920  -0.0591   0.6037   1.0000
   5.000   0.6289   0.05934   0.04837  -0.0603   0.5949   1.0000
   5.250   0.6125   0.06256   0.05159  -0.0578   0.5815   1.0000
   5.500   0.6172   0.06474   0.05377  -0.0565   0.5702   1.0000
   5.750   0.6679   0.06400   0.05303  -0.0570   0.5610   1.0000
   6.000   0.6470   0.06794   0.05697  -0.0549   0.5484   1.0000
   6.250   0.6564   0.07008   0.05912  -0.0540   0.5384   1.0000
   6.500   0.6840   0.07086   0.05992  -0.0536   0.5286   1.0000
   6.750   0.6673   0.07500   0.06408  -0.0524   0.5183   1.0000
   7.000   0.7152   0.07445   0.06355  -0.0524   0.5103   1.0000
   7.250   0.6760   0.08064   0.06975  -0.0514   0.5020   1.0000
   7.500   0.7277   0.07978   0.06892  -0.0511   0.4933   1.0000
   7.750   0.6858   0.08653   0.07568  -0.0507   0.4880   1.0000
   8.000   0.6764   0.09093   0.08011  -0.0509   0.4853   1.0000
   8.250   0.6705   0.09518   0.08440  -0.0512   0.4845   1.0000
   8.500   0.6640   0.09967   0.08892  -0.0518   0.4867   1.0000
   8.750   0.6698   0.10386   0.09316  -0.0528   0.4910   1.0000
   9.000   0.5938   0.11555   0.10497  -0.0579   0.5798   1.0000
   9.250   0.6048   0.11892   0.10836  -0.0583   0.5762   1.0000
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