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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 50,000
Max Cl/Cd: 42.69 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe372-il-50000-n5.txt
Download as CSV file: xf-goe372-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3565   0.10709   0.10038  -0.0294   1.0000   0.0820
  -8.000  -0.3599   0.10527   0.09867  -0.0301   1.0000   0.0824
  -7.750  -0.3639   0.10334   0.09687  -0.0305   1.0000   0.0826
  -7.500  -0.3644   0.10084   0.09447  -0.0318   1.0000   0.0828
  -7.250  -0.3625   0.09804   0.09176  -0.0331   1.0000   0.0829
  -7.000  -0.3596   0.09496   0.08875  -0.0342   1.0000   0.0829
  -6.500  -0.3493   0.08502   0.07888  -0.0357   1.0000   0.0544
  -6.250  -0.3455   0.08173   0.07564  -0.0368   1.0000   0.0544
  -6.000  -0.3402   0.07840   0.07234  -0.0388   1.0000   0.0546
  -5.750  -0.3330   0.07480   0.06875  -0.0410   1.0000   0.0548
  -5.500  -0.3238   0.07102   0.06494  -0.0433   1.0000   0.0549
  -5.250  -0.3147   0.06722   0.06111  -0.0444   1.0000   0.0548
  -5.000  -0.3044   0.06344   0.05728  -0.0454   1.0000   0.0546
  -4.750  -0.2895   0.05918   0.05291  -0.0477   1.0000   0.0546
  -4.500  -0.2842   0.05758   0.05134  -0.0453   1.0000   0.0592
  -4.250  -0.2653   0.05413   0.04772  -0.0478   1.0000   0.0643
  -4.000  -0.2398   0.04937   0.04265  -0.0518   1.0000   0.0658
  -3.750  -0.2052   0.04345   0.03604  -0.0574   1.0000   0.0688
  -3.500  -0.1858   0.04232   0.03493  -0.0575   0.9977   0.0787
  -3.250  -0.1390   0.03724   0.02904  -0.0636   0.9918   0.0805
  -3.000  -0.0936   0.03297   0.02376  -0.0683   0.9863   0.0834
  -2.750  -0.0573   0.03111   0.02158  -0.0709   0.9791   0.0883
  -2.500  -0.0204   0.02969   0.01965  -0.0734   0.9717   0.1003
  -2.250   0.0180   0.02808   0.01758  -0.0759   0.9654   0.1050
  -2.000   0.0544   0.02661   0.01553  -0.0777   0.9578   0.1097
  -1.750   0.0906   0.02553   0.01413  -0.0795   0.9507   0.1157
  -1.500   0.1264   0.02471   0.01294  -0.0810   0.9428   0.1261
  -1.250   0.1621   0.02423   0.01234  -0.0828   0.9348   0.1434
  -1.000   0.2006   0.02370   0.01164  -0.0849   0.9275   0.1633
  -0.750   0.2347   0.02323   0.01105  -0.0862   0.9185   0.1834
  -0.500   0.2742   0.02274   0.01057  -0.0886   0.9117   0.2119
  -0.250   0.3071   0.02229   0.01020  -0.0897   0.9020   0.2426
   0.000   0.3427   0.02169   0.00995  -0.0914   0.8937   0.3122
   0.250   0.3836   0.01988   0.00961  -0.0938   0.8867   1.0000
   0.500   0.4158   0.02005   0.00948  -0.0945   0.8762   1.0000
   0.750   0.4493   0.02020   0.00942  -0.0955   0.8665   1.0000
   1.000   0.4849   0.02030   0.00937  -0.0968   0.8576   1.0000
   1.250   0.5141   0.02050   0.00948  -0.0970   0.8462   1.0000
   1.500   0.5438   0.02069   0.00962  -0.0973   0.8351   1.0000
   1.750   0.5745   0.02087   0.00976  -0.0977   0.8245   1.0000
   2.000   0.6084   0.02098   0.00989  -0.0985   0.8156   1.0000
   2.250   0.6358   0.02123   0.01018  -0.0983   0.8036   1.0000
   2.500   0.6630   0.02151   0.01051  -0.0981   0.7918   1.0000
   2.750   0.6908   0.02178   0.01090  -0.0979   0.7805   1.0000
   3.000   0.7199   0.02201   0.01124  -0.0979   0.7701   1.0000
   3.250   0.7493   0.02224   0.01160  -0.0979   0.7598   1.0000
   3.500   0.7746   0.02259   0.01212  -0.0973   0.7475   1.0000
   3.750   0.8007   0.02286   0.01263  -0.0967   0.7345   1.0000
   4.000   0.8276   0.02299   0.01296  -0.0958   0.7198   1.0000
   4.250   0.8539   0.02283   0.01301  -0.0943   0.6995   1.0000
   4.500   0.8745   0.02165   0.01178  -0.0895   0.6450   1.0000
   4.750   0.8930   0.02135   0.01153  -0.0859   0.5921   1.0000
   5.000   0.9119   0.02136   0.01138  -0.0826   0.5295   1.0000
   5.250   0.9231   0.02203   0.01153  -0.0786   0.4120   1.0000
   5.500   0.9256   0.02417   0.01230  -0.0747   0.2177   1.0000
   5.750   0.9263   0.02753   0.01431  -0.0719   0.0527   1.0000
   6.000   0.9406   0.02921   0.01601  -0.0699   0.0423   1.0000
   6.250   0.9553   0.03072   0.01771  -0.0680   0.0372   1.0000
   6.500   0.9683   0.03238   0.01965  -0.0659   0.0352   1.0000
   6.750   0.9816   0.03390   0.02144  -0.0638   0.0338   1.0000
   7.000   0.9937   0.03555   0.02332  -0.0616   0.0326   1.0000
   7.250   1.0058   0.03726   0.02525  -0.0594   0.0310   1.0000
   7.500   1.0184   0.03918   0.02730  -0.0574   0.0290   1.0000
   7.750   1.0367   0.04141   0.02959  -0.0559   0.0276   1.0000
   8.000   1.0659   0.04349   0.03190  -0.0551   0.0271   1.0000
   8.250   1.0992   0.04612   0.03478  -0.0548   0.0269   1.0000
   8.500   1.1279   0.04914   0.03810  -0.0544   0.0268   1.0000
   8.750   1.1504   0.05247   0.04194  -0.0534   0.0269   1.0000
   9.000   1.1664   0.05582   0.04567  -0.0519   0.0270   1.0000
   9.250   1.1761   0.05920   0.04949  -0.0500   0.0269   1.0000
   9.500   1.1804   0.06257   0.05329  -0.0478   0.0268   1.0000
   9.750   1.1807   0.06603   0.05714  -0.0455   0.0267   1.0000
  10.000   1.1768   0.06949   0.06095  -0.0432   0.0267   1.0000
  10.250   1.1671   0.07283   0.06460  -0.0405   0.0266   1.0000
  10.500   1.1556   0.07630   0.06833  -0.0383   0.0267   1.0000
  10.750   1.1411   0.08004   0.07232  -0.0368   0.0267   1.0000
  11.000   1.1266   0.08414   0.07664  -0.0363   0.0268   1.0000
  11.250   1.1113   0.08862   0.08132  -0.0365   0.0270   1.0000
  11.500   1.0958   0.09352   0.08639  -0.0376   0.0271   1.0000
  11.750   1.0817   0.09875   0.09176  -0.0393   0.0273   1.0000
  12.000   1.0673   0.10444   0.09758  -0.0417   0.0274   1.0000
  12.250   1.0543   0.11048   0.10371  -0.0446   0.0276   1.0000
  12.500   1.0423   0.11669   0.11008  -0.0480   0.0279   1.0000
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