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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 50,000
Max Cl/Cd: 42.1 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe81-il-50000-n5.txt
Download as CSV file: xf-goe81-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2804   0.10692   0.10076  -0.0245   1.0000   0.0714
  -7.250  -0.2927   0.10668   0.10064  -0.0230   1.0000   0.0726
  -7.000  -0.3045   0.10680   0.10089  -0.0227   1.0000   0.0735
  -6.750  -0.2862   0.10623   0.10032  -0.0340   0.9921   0.0745
  -6.500  -0.2765   0.09905   0.09316  -0.0283   0.9896   0.0767
  -6.250  -0.2552   0.09496   0.08904  -0.0316   0.9825   0.0799
  -6.000  -0.2294   0.09143   0.08547  -0.0379   0.9742   0.0841
  -5.750  -0.1833   0.09045   0.08427  -0.0559   0.9610   0.0883
  -5.500  -0.1762   0.08454   0.07848  -0.0518   0.9553   0.0905
  -5.250  -0.1520   0.08063   0.07453  -0.0546   0.9495   0.0963
  -5.000  -0.1060   0.07890   0.07257  -0.0688   0.9382   0.1034
  -4.750  -0.0932   0.07404   0.06779  -0.0669   0.9326   0.1061
  -4.500  -0.0680   0.07092   0.06461  -0.0701   0.9248   0.1122
  -4.250  -0.0247   0.06778   0.06128  -0.0795   0.9184   0.1198
  -4.000  -0.0053   0.06471   0.05820  -0.0801   0.9104   0.1267
  -3.750   0.0340   0.06143   0.05479  -0.0865   0.9055   0.1388
  -3.500   0.0653   0.05920   0.05243  -0.0912   0.8966   0.1517
  -3.250   0.1049   0.05645   0.04952  -0.0967   0.8913   0.1668
  -3.000   0.1342   0.05415   0.04709  -0.0995   0.8828   0.1821
  -2.750   0.1669   0.05105   0.04395  -0.1023   0.8761   0.1995
  -2.500   0.1974   0.04891   0.04169  -0.1049   0.8658   0.2278
  -2.000   0.2470   0.04359   0.03640  -0.1061   0.8479   0.3211
  -1.500   0.3822   0.03979   0.03089  -0.1212   0.8323   0.1016
  -1.250   0.4226   0.03798   0.02860  -0.1232   0.8253   0.0879
  -1.000   0.4517   0.03629   0.02683  -0.1240   0.8163   0.0850
  -0.750   0.4844   0.03500   0.02528  -0.1250   0.8081   0.0842
  -0.500   0.5177   0.03378   0.02381  -0.1259   0.7999   0.0837
  -0.250   0.5479   0.03277   0.02255  -0.1262   0.7907   0.0818
   0.000   0.5826   0.03162   0.02109  -0.1268   0.7832   0.0796
   0.250   0.6105   0.03091   0.02014  -0.1266   0.7730   0.0782
   0.500   0.6455   0.02991   0.01884  -0.1270   0.7661   0.0773
   0.750   0.6711   0.02945   0.01817  -0.1262   0.7549   0.0770
   1.000   0.7007   0.02888   0.01741  -0.1259   0.7457   0.0789
   1.250   0.7309   0.02831   0.01667  -0.1256   0.7366   0.0823
   1.500   0.7568   0.02800   0.01623  -0.1248   0.7254   0.0846
   1.750   0.7862   0.02751   0.01559  -0.1243   0.7163   0.0861
   2.000   0.8137   0.02720   0.01516  -0.1236   0.7056   0.0880
   2.250   0.8392   0.02700   0.01495  -0.1229   0.6939   0.0911
   2.500   0.8674   0.02678   0.01467  -0.1225   0.6833   0.0971
   2.750   0.8966   0.02652   0.01439  -0.1222   0.6729   0.1093
   3.000   0.9219   0.02653   0.01450  -0.1216   0.6602   0.1288
   3.250   0.9435   0.02522   0.01462  -0.1202   0.6486   1.0000
   3.500   0.9716   0.02536   0.01445  -0.1195   0.6379   1.0000
   3.750   0.9970   0.02565   0.01458  -0.1187   0.6258   1.0000
   4.000   1.0204   0.02608   0.01492  -0.1178   0.6128   1.0000
   4.250   1.0446   0.02647   0.01523  -0.1170   0.6006   1.0000
   4.500   1.0707   0.02674   0.01541  -0.1163   0.5896   1.0000
   4.750   1.0948   0.02714   0.01579  -0.1155   0.5776   1.0000
   5.000   1.1165   0.02769   0.01637  -0.1145   0.5650   1.0000
   5.250   1.1391   0.02816   0.01685  -0.1136   0.5529   1.0000
   5.500   1.1630   0.02852   0.01722  -0.1127   0.5414   1.0000
   5.750   1.1875   0.02878   0.01747  -0.1119   0.5298   1.0000
   6.000   1.2081   0.02926   0.01801  -0.1106   0.5163   1.0000
   6.250   1.2289   0.02972   0.01853  -0.1094   0.5029   1.0000
   6.500   1.2501   0.03012   0.01896  -0.1082   0.4896   1.0000
   6.750   1.2715   0.03050   0.01937  -0.1069   0.4761   1.0000
   7.000   1.2928   0.03090   0.01978  -0.1057   0.4626   1.0000
   7.250   1.3143   0.03132   0.02025  -0.1044   0.4495   1.0000
   7.500   1.3367   0.03175   0.02068  -0.1034   0.4370   1.0000
   7.750   1.3550   0.03251   0.02156  -0.1020   0.4244   1.0000
   8.000   1.3731   0.03333   0.02251  -0.1007   0.4125   1.0000
   8.250   1.3923   0.03408   0.02339  -0.0994   0.4007   1.0000
   8.500   1.4117   0.03478   0.02416  -0.0981   0.3884   1.0000
   8.750   1.4266   0.03566   0.02517  -0.0963   0.3749   1.0000
   9.000   1.4380   0.03668   0.02636  -0.0942   0.3609   1.0000
   9.250   1.4482   0.03773   0.02761  -0.0920   0.3470   1.0000
   9.500   1.4572   0.03883   0.02887  -0.0896   0.3333   1.0000
   9.750   1.4643   0.03998   0.03016  -0.0871   0.3200   1.0000
  10.000   1.4696   0.04119   0.03149  -0.0844   0.3070   1.0000
  10.250   1.4746   0.04248   0.03288  -0.0818   0.2942   1.0000
  10.500   1.4799   0.04381   0.03427  -0.0795   0.2818   1.0000
  10.750   1.4806   0.04566   0.03633  -0.0771   0.2693   1.0000
  11.000   1.4816   0.04759   0.03840  -0.0750   0.2573   1.0000
  11.250   1.4840   0.04949   0.04039  -0.0731   0.2464   1.0000
  11.500   1.4878   0.05126   0.04219  -0.0713   0.2360   1.0000
  11.750   1.4843   0.05395   0.04508  -0.0697   0.2252   1.0000
  12.000   1.4812   0.05655   0.04777  -0.0683   0.2148   1.0000
  12.250   1.4782   0.05910   0.05033  -0.0670   0.2043   1.0000
  12.500   1.4707   0.06252   0.05397  -0.0662   0.1942   1.0000
  12.750   1.4635   0.06600   0.05757  -0.0656   0.1846   1.0000
  13.000   1.4572   0.06936   0.06097  -0.0652   0.1754   1.0000
  13.250   1.4480   0.07344   0.06523  -0.0652   0.1666   1.0000
  13.500   1.4395   0.07749   0.06940  -0.0653   0.1585   1.0000
  13.750   1.4325   0.08126   0.07321  -0.0654   0.1505   1.0000
  14.000   1.4220   0.08604   0.07821  -0.0661   0.1432   1.0000
  14.250   1.4170   0.08964   0.08175  -0.0663   0.1356   1.0000
  14.500   1.4038   0.09524   0.08763  -0.0677   0.1283   1.0000
  14.750   1.3963   0.09945   0.09176  -0.0686   0.1198   1.0000
  15.000   1.3815   0.10574   0.09834  -0.0708   0.1124   1.0000
  15.250   1.3732   0.11048   0.10304  -0.0723   0.1042   1.0000
  15.500   1.3580   0.11741   0.11030  -0.0752   0.0971   1.0000
  15.750   1.3480   0.12309   0.11607  -0.0775   0.0896   1.0000
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