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UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)
Reynolds number: 500,000
Max Cl/Cd: 75.92 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ua79sf18-il-500000-n5.txt
Download as CSV file: xf-ua79sf18-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1022   0.08894   0.08525  -0.1403   0.7728   0.0030
 -12.500  -0.1193   0.08072   0.07707  -0.1437   0.7724   0.0029
 -12.250  -0.1496   0.06708   0.06341  -0.1508   0.7720   0.0027
 -12.000  -0.1860   0.05795   0.05415  -0.1552   0.7715   0.0027
 -11.750  -0.2091   0.05285   0.04894  -0.1566   0.7709   0.0026
 -11.500  -0.2293   0.04871   0.04467  -0.1567   0.7702   0.0025
 -11.250  -0.2503   0.04478   0.04060  -0.1558   0.7695   0.0025
 -11.000  -0.2679   0.04141   0.03706  -0.1543   0.7688   0.0025
 -10.750  -0.2861   0.03805   0.03349  -0.1520   0.7680   0.0025
 -10.500  -0.2969   0.03545   0.03070  -0.1496   0.7672   0.0026
 -10.250  -0.3028   0.03327   0.02833  -0.1471   0.7663   0.0028
 -10.000  -0.3071   0.03095   0.02577  -0.1445   0.7655   0.0026
  -9.750  -0.3066   0.02897   0.02357  -0.1419   0.7647   0.0027
  -9.500  -0.3009   0.02734   0.02173  -0.1398   0.7640   0.0027
  -9.250  -0.2916   0.02597   0.02018  -0.1380   0.7633   0.0029
  -9.000  -0.2791   0.02459   0.01861  -0.1364   0.7628   0.0031
  -8.750  -0.2631   0.02322   0.01705  -0.1353   0.7624   0.0030
  -8.500  -0.2457   0.02223   0.01592  -0.1343   0.7619   0.0033
  -8.250  -0.2271   0.02137   0.01493  -0.1334   0.7615   0.0034
  -8.000  -0.2078   0.02055   0.01397  -0.1325   0.7611   0.0035
  -7.750  -0.1887   0.01969   0.01299  -0.1316   0.7606   0.0036
  -7.500  -0.1713   0.01960   0.01285  -0.1305   0.7601   0.0038
  -7.250  -0.1535   0.01868   0.01183  -0.1293   0.7595   0.0041
  -7.000  -0.1447   0.01772   0.01080  -0.1266   0.7587   0.0045
  -6.750  -0.1349   0.01720   0.01023  -0.1240   0.7579   0.0046
  -6.500  -0.1222   0.01672   0.00971  -0.1219   0.7572   0.0047
  -6.250  -0.1080   0.01628   0.00922  -0.1200   0.7564   0.0048
  -6.000  -0.0920   0.01590   0.00878  -0.1184   0.7557   0.0048
  -5.750  -0.0751   0.01554   0.00836  -0.1169   0.7549   0.0049
  -5.500  -0.0565   0.01523   0.00800  -0.1157   0.7541   0.0051
  -5.250  -0.0368   0.01495   0.00766  -0.1146   0.7534   0.0053
  -5.000  -0.0158   0.01472   0.00738  -0.1138   0.7527   0.0056
  -4.750   0.0062   0.01451   0.00711  -0.1132   0.7520   0.0060
  -4.500   0.0287   0.01429   0.00685  -0.1126   0.7513   0.0071
  -4.250   0.0518   0.01410   0.00664  -0.1121   0.7507   0.0102
  -4.000   0.0712   0.01366   0.00636  -0.1112   0.7500   0.0516
  -3.750   0.0922   0.01330   0.00616  -0.1106   0.7495   0.0984
  -3.500   0.1025   0.01215   0.00575  -0.1087   0.7488   0.2866
  -3.250   0.1088   0.01092   0.00579  -0.1058   0.7482   0.6209
  -3.000   0.1374   0.01119   0.00596  -0.1062   0.7478   0.6428
  -2.750   0.1659   0.01135   0.00607  -0.1065   0.7474   0.6514
  -2.500   0.1944   0.01152   0.00615  -0.1069   0.7469   0.6600
  -2.250   0.2197   0.01168   0.00634  -0.1067   0.7461   0.6653
  -2.000   0.2432   0.01187   0.00653  -0.1063   0.7448   0.6697
  -1.750   0.2675   0.01205   0.00664  -0.1060   0.7435   0.6731
  -1.500   0.2925   0.01215   0.00674  -0.1059   0.7423   0.6753
  -1.250   0.3183   0.01223   0.00682  -0.1059   0.7411   0.6775
  -1.000   0.3449   0.01228   0.00686  -0.1060   0.7400   0.6798
  -0.750   0.3725   0.01230   0.00684  -0.1063   0.7389   0.6818
  -0.500   0.4008   0.01228   0.00680  -0.1069   0.7380   0.6828
  -0.250   0.4294   0.01227   0.00675  -0.1074   0.7373   0.6834
   0.000   0.4583   0.01225   0.00670  -0.1080   0.7366   0.6841
   0.250   0.4875   0.01223   0.00665  -0.1087   0.7359   0.6847
   0.500   0.5175   0.01217   0.00657  -0.1096   0.7353   0.6851
   0.750   0.5478   0.01212   0.00649  -0.1105   0.7347   0.6856
   1.000   0.5640   0.01241   0.00682  -0.1087   0.7318   0.6863
   1.250   0.5837   0.01260   0.00704  -0.1077   0.7293   0.6869
   1.500   0.6092   0.01261   0.00705  -0.1076   0.7276   0.6874
   2.000   0.6676   0.01238   0.00683  -0.1089   0.7250   0.6882
   2.250   0.6984   0.01223   0.00668  -0.1099   0.7239   0.6886
   2.500   0.7303   0.01203   0.00650  -0.1110   0.7229   0.6890
   2.750   0.7637   0.01182   0.00629  -0.1124   0.7219   0.6891
   3.000   0.7671   0.01219   0.00676  -0.1082   0.7164   0.6894
   3.250   0.7933   0.01203   0.00663  -0.1081   0.7137   0.6898
   3.500   0.8397   0.01106   0.00560  -0.1117   0.7088   0.6900
   3.750   0.8277   0.01104   0.00562  -0.1038   0.6909   0.6903
   4.000   0.8077   0.01184   0.00649  -0.0952   0.6778   0.6906
   4.500   0.8353   0.01163   0.00575  -0.0900   0.5853   0.6910
   4.750   0.8115   0.01326   0.00713  -0.0819   0.5481   0.6913
   5.000   0.7972   0.01472   0.00840  -0.0756   0.5102   0.6916
   5.250   0.7950   0.01582   0.00938  -0.0714   0.4830   0.6918
   5.500   0.7724   0.01776   0.01101  -0.0643   0.4305   0.6921
   5.750   0.7714   0.01893   0.01201  -0.0606   0.3962   0.6923
   6.000   0.7669   0.02030   0.01316  -0.0565   0.3521   0.6925
   6.250   0.7617   0.02180   0.01434  -0.0524   0.2961   0.6928
   6.500   0.7302   0.02471   0.01638  -0.0451   0.1449   0.6930
   6.750   0.7249   0.02651   0.01770  -0.0415   0.0494   0.6932
   7.000   0.7347   0.02755   0.01860  -0.0397   0.0064   0.6934
   7.250   0.7531   0.02811   0.01920  -0.0390   0.0054   0.6936
   7.500   0.7717   0.02866   0.01978  -0.0384   0.0052   0.6938
   7.750   0.7899   0.02925   0.02045  -0.0378   0.0048   0.6941
   8.000   0.8076   0.02987   0.02113  -0.0371   0.0046   0.6943
   8.250   0.8245   0.03056   0.02187  -0.0363   0.0044   0.6945
   8.500   0.8411   0.03127   0.02265  -0.0356   0.0042   0.6948
   8.750   0.8570   0.03204   0.02349  -0.0347   0.0039   0.6951
   9.000   0.8690   0.03311   0.02468  -0.0334   0.0029   0.6953
   9.250   0.8842   0.03396   0.02559  -0.0325   0.0030   0.6956
   9.500   0.8920   0.03536   0.02711  -0.0309   0.0026   0.6959
   9.750   0.9033   0.03654   0.02835  -0.0296   0.0026   0.6961
  10.000   0.9184   0.03746   0.02934  -0.0289   0.0025   0.6964
  10.250   0.9277   0.03883   0.03079  -0.0276   0.0025   0.6968
  10.500   0.9391   0.04009   0.03211  -0.0265   0.0022   0.6970
  10.750   0.9479   0.04157   0.03367  -0.0253   0.0021   0.6973
  11.000   0.9553   0.04319   0.03536  -0.0240   0.0021   0.6977
  11.250   0.9629   0.04484   0.03708  -0.0228   0.0021   0.6980
  11.500   0.9703   0.04654   0.03886  -0.0216   0.0021   0.6983
  11.750   0.9758   0.04846   0.04086  -0.0204   0.0020   0.6987
  12.000   0.9841   0.05014   0.04262  -0.0194   0.0020   0.6990
  12.250   0.9906   0.05205   0.04460  -0.0183   0.0020   0.6994
  12.500   0.9990   0.05381   0.04644  -0.0174   0.0020   0.6998
  12.750   1.0083   0.05552   0.04826  -0.0166   0.0020   0.7003
  13.000   1.0183   0.05719   0.05001  -0.0159   0.0020   0.7008
  13.250   1.0295   0.05881   0.05171  -0.0152   0.0020   0.7013
  13.750   1.0545   0.06196   0.05507  -0.0140   0.0020   0.7025
  14.000   1.0674   0.06363   0.05685  -0.0135   0.0020   0.7030
  14.250   1.0791   0.06545   0.05880  -0.0131   0.0021   0.7036
  14.500   1.0903   0.06750   0.06101  -0.0126   0.0021   0.7041
  14.750   1.0986   0.06983   0.06350  -0.0121   0.0021   0.7048
  15.000   1.1040   0.07242   0.06625  -0.0118   0.0022   0.7054
  15.250   1.1071   0.07559   0.06963  -0.0113   0.0022   0.7060
  15.500   1.1068   0.07907   0.07331  -0.0109   0.0023   0.7067
  15.750   1.1038   0.08279   0.07722  -0.0108   0.0023   0.7075
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