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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 100,000
Max Cl/Cd: 57.97 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74080-il-100000-n5.txt
Download as CSV file: xf-fx74080-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 74-080                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2853   0.10200   0.09731  -0.0586   0.9721   0.0289
  -8.250  -0.2730   0.09887   0.09419  -0.0639   0.9670   0.0295
  -8.000  -0.2624   0.09571   0.09103  -0.0690   0.9607   0.0298
  -7.750  -0.2499   0.09243   0.08777  -0.0756   0.9542   0.0301
  -7.500  -0.2342   0.08848   0.08381  -0.0821   0.9485   0.0302
  -7.250  -0.2180   0.08448   0.07977  -0.0877   0.9434   0.0303
  -7.000  -0.2143   0.07920   0.07456  -0.0816   0.9426   0.0339
  -6.750  -0.1955   0.07529   0.07062  -0.0873   0.9392   0.0390
  -6.500  -0.1849   0.07212   0.06741  -0.0911   0.9322   0.0398
  -6.250  -0.1517   0.06813   0.06318  -0.1053   0.9264   0.0432
  -6.000  -0.1374   0.06524   0.06009  -0.1086   0.9195   0.0435
  -5.750  -0.1274   0.05973   0.05470  -0.1090   0.9162   0.0447
  -5.500  -0.1094   0.05594   0.05087  -0.1105   0.9136   0.0464
  -5.250  -0.0959   0.05300   0.04784  -0.1114   0.9083   0.0479
  -5.000  -0.0759   0.04960   0.04428  -0.1135   0.9038   0.0491
  -4.750  -0.0400   0.04441   0.03860  -0.1172   0.9007   0.0288
  -4.500  -0.0230   0.04122   0.03523  -0.1177   0.8964   0.0265
  -4.250  -0.0025   0.03807   0.03169  -0.1181   0.8917   0.0245
  -4.000   0.0264   0.03463   0.02783  -0.1195   0.8888   0.0227
  -3.750   0.0587   0.03130   0.02396  -0.1210   0.8866   0.0211
  -3.500   0.0779   0.02909   0.02128  -0.1194   0.8815   0.0203
  -3.250   0.1040   0.02702   0.01875  -0.1192   0.8780   0.0202
  -3.000   0.1343   0.02504   0.01631  -0.1196   0.8756   0.0204
  -2.750   0.1660   0.02344   0.01435  -0.1203   0.8737   0.0217
  -2.500   0.1868   0.02295   0.01362  -0.1191   0.8693   0.0283
  -2.250   0.2117   0.02200   0.01239  -0.1182   0.8655   0.0303
  -2.000   0.2391   0.02054   0.01086  -0.1181   0.8629   0.0327
  -1.750   0.2685   0.01969   0.00990  -0.1185   0.8608   0.0369
  -1.500   0.2891   0.01924   0.00924  -0.1171   0.8565   0.0477
  -1.250   0.3114   0.01875   0.00887  -0.1162   0.8522   0.0912
  -1.000   0.3461   0.01611   0.00876  -0.1170   0.8513   1.0000
  -0.750   0.3755   0.01620   0.00853  -0.1174   0.8486   1.0000
  -0.500   0.4070   0.01627   0.00835  -0.1183   0.8465   1.0000
  -0.250   0.4205   0.01669   0.00862  -0.1159   0.8398   1.0000
   0.000   0.4482   0.01683   0.00858  -0.1161   0.8365   1.0000
   0.250   0.4789   0.01692   0.00852  -0.1169   0.8342   1.0000
   0.500   0.4958   0.01732   0.00883  -0.1152   0.8282   1.0000
   0.750   0.5216   0.01752   0.00895  -0.1150   0.8242   1.0000
   1.000   0.5517   0.01763   0.00900  -0.1156   0.8216   1.0000
   1.250   0.5711   0.01800   0.00934  -0.1144   0.8161   1.0000
   1.500   0.5946   0.01828   0.00962  -0.1139   0.8115   1.0000
   1.750   0.6241   0.01841   0.00975  -0.1144   0.8087   1.0000
   2.250   0.6671   0.01909   0.01048  -0.1126   0.7983   1.0000
   2.500   0.6970   0.01921   0.01066  -0.1131   0.7954   1.0000
   2.750   0.7146   0.01967   0.01119  -0.1116   0.7889   1.0000
   3.000   0.7394   0.01993   0.01165  -0.1113   0.7843   1.0000
   3.250   0.7703   0.02002   0.01186  -0.1119   0.7816   1.0000
   3.500   0.7837   0.02063   0.01259  -0.1097   0.7736   1.0000
   3.750   0.8123   0.02077   0.01289  -0.1099   0.7698   1.0000
   4.250   0.8562   0.02141   0.01395  -0.1081   0.7576   1.0000
   4.500   0.8973   0.01858   0.01133  -0.1066   0.7255   1.0000
   4.750   0.9194   0.01586   0.00790  -0.0997   0.5045   1.0000
   5.000   0.8907   0.01899   0.00897  -0.0903   0.1951   1.0000
   5.250   0.8822   0.02148   0.01040  -0.0846   0.0412   1.0000
   5.500   0.8931   0.02263   0.01159  -0.0818   0.0274   1.0000
   5.750   0.9048   0.02375   0.01291  -0.0790   0.0236   1.0000
   6.000   0.9125   0.02516   0.01449  -0.0759   0.0213   1.0000
   6.250   0.9169   0.02703   0.01646  -0.0723   0.0200   1.0000
   6.500   0.9317   0.02854   0.01809  -0.0702   0.0190   1.0000
   6.750   0.9528   0.02984   0.01952  -0.0690   0.0160   1.0000
   7.000   0.9775   0.03140   0.02119  -0.0686   0.0129   1.0000
   7.250   1.0214   0.03413   0.02412  -0.0707   0.0123   1.0000
   7.500   1.0664   0.03757   0.02790  -0.0730   0.0121   1.0000
   7.750   1.0970   0.04084   0.03156  -0.0730   0.0121   1.0000
   8.000   1.1202   0.04433   0.03571  -0.0717   0.0126   1.0000
   8.250   1.1360   0.04777   0.03963  -0.0695   0.0129   1.0000
   8.500   1.1464   0.05131   0.04361  -0.0668   0.0134   1.0000
   8.750   1.1524   0.05478   0.04749  -0.0637   0.0140   1.0000
   9.000   1.1537   0.05833   0.05141  -0.0603   0.0144   1.0000
   9.250   1.1512   0.06182   0.05523  -0.0568   0.0149   1.0000
   9.500   1.1442   0.06492   0.05861  -0.0529   0.0152   1.0000
   9.750   1.1330   0.06819   0.06212  -0.0490   0.0156   1.0000
  10.000   1.1203   0.07141   0.06558  -0.0455   0.0159   1.0000
  10.250   1.1058   0.07482   0.06919  -0.0427   0.0161   1.0000
  10.500   1.0898   0.07850   0.07307  -0.0404   0.0164   1.0000
  10.750   1.0726   0.08248   0.07724  -0.0389   0.0166   1.0000
  11.000   1.0553   0.08670   0.08163  -0.0381   0.0167   1.0000
  11.250   1.0371   0.09136   0.08644  -0.0382   0.0168   1.0000
  11.500   1.0184   0.09653   0.09175  -0.0391   0.0169   1.0000
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