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EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 748 AIRFOIL (e748-il)
Reynolds number: 100,000
Max Cl/Cd: 31.42 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e748-il-100000.txt
Download as CSV file: xf-e748-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 748 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5865   0.07447   0.06888  -0.0806   1.0000   0.0639
 -12.000  -0.6064   0.07035   0.06471  -0.0810   1.0000   0.0636
 -11.750  -0.6330   0.06640   0.06070  -0.0811   1.0000   0.0633
 -11.500  -0.6580   0.06320   0.05744  -0.0803   1.0000   0.0630
 -11.250  -0.6857   0.06065   0.05485  -0.0785   1.0000   0.0628
 -11.000  -0.7156   0.05885   0.05303  -0.0755   1.0000   0.0626
 -10.750  -0.7448   0.05712   0.05127  -0.0728   1.0000   0.0624
 -10.500  -0.7680   0.05492   0.04895  -0.0714   1.0000   0.0623
 -10.250  -0.7841   0.05283   0.04672  -0.0700   1.0000   0.0623
 -10.000  -0.7676   0.04910   0.04250  -0.0755   0.9933   0.0633
  -9.750  -0.7342   0.04564   0.03871  -0.0809   0.9840   0.0648
  -9.500  -0.6967   0.04358   0.03666  -0.0843   0.9752   0.0672
  -9.250  -0.6584   0.04140   0.03430  -0.0880   0.9665   0.0695
  -9.000  -0.6189   0.03920   0.03179  -0.0915   0.9579   0.0723
  -8.750  -0.5855   0.03753   0.03024  -0.0925   0.9480   0.0755
  -8.500  -0.5489   0.03604   0.02872  -0.0948   0.9383   0.0812
  -8.250  -0.5094   0.03455   0.02740  -0.0971   0.9305   0.0893
  -8.000  -0.4799   0.03316   0.02614  -0.0979   0.9188   0.0998
  -7.750  -0.4478   0.03139   0.02449  -0.1001   0.9082   0.1200
  -7.500  -0.4092   0.02857   0.02211  -0.1057   0.9000   0.1604
  -7.250  -0.3746   0.02554   0.01968  -0.1119   0.8881   0.2316
  -7.000  -0.3202   0.02657   0.02127  -0.1152   0.8826   0.3255
  -6.750  -0.2836   0.02935   0.02406  -0.1127   0.8703   0.3502
  -6.500  -0.2265   0.03173   0.02629  -0.1138   0.8658   0.3712
  -6.250  -0.1874   0.03423   0.02878  -0.1108   0.8547   0.3790
  -6.000  -0.1303   0.03581   0.03020  -0.1123   0.8491   0.3940
  -5.750  -0.0919   0.03632   0.03053  -0.1132   0.8372   0.4099
  -5.500  -0.0306   0.03923   0.03339  -0.1105   0.8308   0.4136
  -5.250   0.0002   0.03888   0.03287  -0.1118   0.8168   0.4296
  -5.000   0.0526   0.04075   0.03463  -0.1092   0.8065   0.4355
  -4.750   0.0852   0.04019   0.03388  -0.1106   0.7939   0.4505
  -4.500   0.1014   0.03917   0.03269  -0.1118   0.7793   0.4661
  -4.250   0.1399   0.04037   0.03381  -0.1079   0.7675   0.4721
  -4.000   0.1637   0.03935   0.03259  -0.1096   0.7564   0.4864
  -3.750   0.1860   0.03972   0.03291  -0.1063   0.7437   0.4944
  -3.500   0.2561   0.04356   0.03667  -0.0987   0.7332   0.5614
  -3.250   0.2743   0.04255   0.03554  -0.0982   0.7222   0.5653
  -3.000   0.2424   0.03735   0.03014  -0.1073   0.7126   0.5229
  -2.750   0.2677   0.03744   0.03015  -0.1047   0.7034   0.5295
  -2.500   0.2855   0.03643   0.02902  -0.1063   0.6943   0.5353
  -2.250   0.3085   0.03521   0.02765  -0.1090   0.6855   0.5409
  -2.000   0.3295   0.03523   0.02762  -0.1064   0.6775   0.5456
  -1.750   0.3504   0.03465   0.02697  -0.1066   0.6687   0.5498
  -1.500   0.3833   0.03372   0.02582  -0.1102   0.6622   0.5535
  -1.250   0.4074   0.03283   0.02484  -0.1135   0.6531   0.5570
  -1.000   0.4365   0.03225   0.02414  -0.1144   0.6467   0.5595
  -0.750   0.4557   0.03214   0.02403  -0.1131   0.6393   0.5622
  -0.500   0.4799   0.03187   0.02370  -0.1132   0.6319   0.5653
  -0.250   0.5159   0.03135   0.02300  -0.1159   0.6265   0.5674
   0.000   0.5370   0.03119   0.02286  -0.1164   0.6190   0.5698
   0.250   0.5699   0.03080   0.02234  -0.1190   0.6124   0.5728
   0.500   0.6103   0.03035   0.02166  -0.1228   0.6072   0.5748
   0.750   0.6321   0.03033   0.02169  -0.1234   0.5995   0.5767
   1.000   0.6575   0.03026   0.02160  -0.1231   0.5939   0.5791
   1.250   0.6908   0.03016   0.02138  -0.1244   0.5896   0.5817
   1.500   0.7085   0.03045   0.02177  -0.1237   0.5826   0.5835
   1.750   0.7374   0.03044   0.02172  -0.1247   0.5767   0.5855
   2.000   0.7743   0.03029   0.02142  -0.1270   0.5722   0.5881
   2.250   0.7959   0.03071   0.02189  -0.1271   0.5662   0.5911
   2.500   0.8235   0.03099   0.02215  -0.1283   0.5603   0.5942
   2.750   0.8550   0.03096   0.02206  -0.1293   0.5557   0.5965
   3.000   0.8840   0.03116   0.02223  -0.1298   0.5514   0.5988
   3.250   0.8967   0.03190   0.02313  -0.1282   0.5448   0.6009
   3.500   0.9240   0.03217   0.02340  -0.1287   0.5400   0.6038
   3.750   0.9596   0.03223   0.02337  -0.1304   0.5362   0.6076
   4.000   0.9779   0.03308   0.02429  -0.1299   0.5308   0.6112
   4.250   0.9948   0.03384   0.02514  -0.1290   0.5248   0.6143
   4.500   1.0234   0.03401   0.02532  -0.1293   0.5205   0.6177
   4.750   1.0596   0.03408   0.02533  -0.1308   0.5173   0.6216
   5.000   1.0588   0.03576   0.02724  -0.1276   0.5111   0.6243
   5.250   1.0763   0.03662   0.02816  -0.1269   0.5056   0.6281
   5.500   1.1121   0.03665   0.02813  -0.1284   0.5018   0.6328
   5.750   1.1502   0.03661   0.02806  -0.1298   0.4988   0.6381
   6.000   1.1184   0.03988   0.03170  -0.1230   0.4912   0.6403
   6.250   1.1383   0.04065   0.03252  -0.1225   0.4864   0.6459
   6.500   1.1825   0.04022   0.03204  -0.1248   0.4832   0.6526
   6.750   1.2278   0.03992   0.03170  -0.1271   0.4806   0.6596
   7.000   1.0661   0.05061   0.04290  -0.1080   0.4674   0.6541
   7.250   1.1480   0.04752   0.03978  -0.1129   0.4662   0.6644
   7.500   1.2281   0.04525   0.03748  -0.1186   0.4645   0.6753
   7.750   0.9856   0.06726   0.05980  -0.1025   0.4447   0.6618
   8.000   1.0515   0.06306   0.05565  -0.1028   0.4447   0.6724
   8.250   1.1281   0.05858   0.05118  -0.1044   0.4447   0.6867
   8.500   1.2279   0.05319   0.04580  -0.1087   0.4450   0.7064
   8.750   0.8740   0.09518   0.08800  -0.1046   0.4112   0.6698
   9.000   0.8033   0.10756   0.10046  -0.1073   0.4036   0.6667
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