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GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 414 AIRFOIL (goe414-il)
Reynolds number: 50,000
Max Cl/Cd: 28.74 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe414-il-50000-n5.txt
Download as CSV file: xf-goe414-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 414 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3435   0.11377   0.10764  -0.0398   1.0000   0.0634
  -9.000  -0.3529   0.11147   0.10543  -0.0383   1.0000   0.0630
  -8.750  -0.3636   0.10920   0.10325  -0.0368   1.0000   0.0625
  -8.500  -0.3620   0.10516   0.09924  -0.0395   0.9958   0.0620
  -8.250  -0.3573   0.10046   0.09453  -0.0439   0.9889   0.0619
  -8.000  -0.3562   0.09579   0.08988  -0.0484   0.9808   0.0623
  -7.750  -0.3530   0.09019   0.08429  -0.0549   0.9721   0.0631
  -7.500  -0.3465   0.08335   0.07741  -0.0630   0.9630   0.0638
  -7.250  -0.3430   0.07637   0.07038  -0.0698   0.9527   0.0642
  -7.000  -0.3379   0.06855   0.06235  -0.0767   0.9436   0.0644
  -6.750  -0.3283   0.06047   0.05384  -0.0834   0.9356   0.0650
  -6.500  -0.3102   0.05897   0.05231  -0.0838   0.9277   0.0677
  -6.250  -0.2877   0.05546   0.04851  -0.0869   0.9210   0.0717
  -6.000  -0.2722   0.05026   0.04275  -0.0896   0.9127   0.0742
  -5.750  -0.2474   0.04475   0.03627  -0.0930   0.9066   0.0776
  -5.500  -0.2229   0.04350   0.03497  -0.0937   0.8996   0.0824
  -5.250  -0.1952   0.04119   0.03219  -0.0950   0.8929   0.0878
  -5.000  -0.1610   0.03823   0.02846  -0.0972   0.8882   0.0931
  -4.500  -0.1017   0.03575   0.02551  -0.0989   0.8730   0.1103
  -4.250  -0.0707   0.03435   0.02370  -0.0996   0.8638   0.1217
  -4.000  -0.0400   0.03331   0.02254  -0.1002   0.8545   0.1344
  -3.750  -0.0016   0.03240   0.02145  -0.1021   0.8474   0.1541
  -3.500   0.0237   0.03203   0.02108  -0.1019   0.8366   0.1745
  -3.250   0.0643   0.03126   0.02010  -0.1041   0.8316   0.1965
  -3.000   0.0864   0.03087   0.01963  -0.1031   0.8211   0.2069
  -2.750   0.1261   0.03011   0.01871  -0.1049   0.8167   0.2229
  -2.500   0.1483   0.02991   0.01843  -0.1040   0.8060   0.2389
  -2.250   0.1818   0.02938   0.01781  -0.1048   0.7996   0.2604
  -2.000   0.2084   0.02904   0.01748  -0.1045   0.7906   0.2843
  -1.750   0.2377   0.02864   0.01709  -0.1047   0.7830   0.3213
  -1.500   0.2661   0.02820   0.01675  -0.1048   0.7749   0.3689
  -1.250   0.2913   0.02780   0.01653  -0.1043   0.7662   0.4249
  -1.000   0.3195   0.02704   0.01617  -0.1040   0.7592   0.5142
  -0.750   0.3623   0.02580   0.01602  -0.1055   0.7512   1.0000
  -0.500   0.3939   0.02573   0.01560  -0.1060   0.7437   1.0000
  -0.250   0.4163   0.02597   0.01557  -0.1051   0.7333   1.0000
   0.000   0.4513   0.02579   0.01509  -0.1060   0.7273   1.0000
   0.250   0.4715   0.02611   0.01523  -0.1049   0.7162   1.0000
   0.500   0.4986   0.02621   0.01513  -0.1046   0.7076   1.0000
   0.750   0.5276   0.02624   0.01496  -0.1047   0.6995   1.0000
   1.000   0.5506   0.02651   0.01508  -0.1039   0.6895   1.0000
   1.250   0.5842   0.02638   0.01477  -0.1046   0.6832   1.0000
   1.500   0.6047   0.02680   0.01508  -0.1035   0.6727   1.0000
   1.750   0.6400   0.02665   0.01477  -0.1044   0.6673   1.0000
   2.000   0.6584   0.02721   0.01526  -0.1031   0.6566   1.0000
   2.250   0.6868   0.02738   0.01532  -0.1032   0.6493   1.0000
   2.500   0.7111   0.02773   0.01559  -0.1027   0.6407   1.0000
   2.750   0.7366   0.02807   0.01585  -0.1024   0.6330   1.0000
   3.000   0.7615   0.02845   0.01619  -0.1020   0.6254   1.0000
   3.250   0.7875   0.02884   0.01652  -0.1018   0.6188   1.0000
   3.500   0.8084   0.02945   0.01713  -0.1010   0.6109   1.0000
   3.750   0.8428   0.02947   0.01709  -0.1019   0.6063   1.0000
   4.000   0.8527   0.03063   0.01829  -0.0998   0.5967   1.0000
   4.250   0.8845   0.03078   0.01841  -0.1003   0.5920   1.0000
   4.500   0.8940   0.03205   0.01977  -0.0983   0.5837   1.0000
   4.750   0.9204   0.03249   0.02022  -0.0982   0.5784   1.0000
   5.000   0.9379   0.03339   0.02116  -0.0971   0.5720   1.0000
   5.250   0.9530   0.03441   0.02225  -0.0957   0.5652   1.0000
   5.500   0.9854   0.03455   0.02244  -0.0964   0.5613   1.0000
   5.750   0.9825   0.03655   0.02455  -0.0930   0.5525   1.0000
   6.000   1.0106   0.03685   0.02490  -0.0931   0.5477   1.0000
   6.250   1.0122   0.03847   0.02662  -0.0901   0.5392   1.0000
   6.500   1.0399   0.03860   0.02683  -0.0899   0.5331   1.0000
   6.750   1.0398   0.04025   0.02857  -0.0868   0.5242   1.0000
   7.000   1.0673   0.04035   0.02876  -0.0865   0.5183   1.0000
   7.250   1.0641   0.04242   0.03093  -0.0835   0.5098   1.0000
   7.500   1.0856   0.04297   0.03162  -0.0827   0.5041   1.0000
   7.750   1.0879   0.04490   0.03367  -0.0805   0.4967   1.0000
   8.000   1.0973   0.04639   0.03528  -0.0789   0.4899   1.0000
   8.250   1.1371   0.04568   0.03472  -0.0795   0.4868   1.0000
   8.500   1.1057   0.05037   0.03952  -0.0754   0.4754   1.0000
   8.750   1.1437   0.04963   0.03897  -0.0757   0.4723   1.0000
   9.250   1.1460   0.05437   0.04401  -0.0722   0.4575   1.0000
   9.750   1.1253   0.06185   0.05173  -0.0688   0.4385   1.0000
  10.250   1.1527   0.06458   0.05482  -0.0670   0.4262   1.0000
  10.500   1.1174   0.07178   0.06208  -0.0659   0.4123   1.0000
  11.000   1.1145   0.07870   0.06930  -0.0647   0.3960   1.0000
  11.500   1.0683   0.09168   0.08240  -0.0650   0.3731   1.0000
  13.000   1.1388   0.09184   0.08368  -0.0563   0.2871   1.0000
  13.250   1.1534   0.09123   0.08324  -0.0550   0.2637   1.0000
  13.500   1.1568   0.09292   0.08500  -0.0543   0.2321   1.0000
  13.750   1.1526   0.09606   0.08801  -0.0542   0.1858   1.0000
  14.000   1.1402   0.09955   0.09032  -0.0535   0.0990   1.0000
  14.250   1.1265   0.10498   0.09560  -0.0544   0.0753   1.0000
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