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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 100,000
Max Cl/Cd: 105.59 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e376-il-100000.txt
Download as CSV file: xf-e376-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 376 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.1892   0.09558   0.09166  -0.0184   1.0000   0.0186
  -6.750  -0.1953   0.09494   0.09120  -0.0168   1.0000   0.0190
  -6.500  -0.1867   0.09340   0.08971  -0.0194   0.9910   0.0195
  -6.250  -0.1423   0.08919   0.08546  -0.0295   0.9773   0.0210
  -6.000  -0.0870   0.08620   0.08239  -0.0422   0.9636   0.0222
  -5.750  -0.0203   0.08601   0.08208  -0.0585   0.9460   0.0228
  -5.250   0.0353   0.07578   0.07179  -0.0670   0.9146   0.0235
  -5.000   0.0510   0.07117   0.06713  -0.0677   0.8982   0.0243
  -4.750   0.0700   0.06837   0.06426  -0.0695   0.8797   0.0251
  -4.500   0.0919   0.06593   0.06175  -0.0719   0.8634   0.0262
  -4.250   0.1148   0.06371   0.05942  -0.0743   0.8483   0.0272
  -4.000   0.1392   0.06157   0.05720  -0.0770   0.8347   0.0285
  -3.750   0.1653   0.05954   0.05507  -0.0798   0.8223   0.0298
  -3.500   0.1948   0.05775   0.05316  -0.0831   0.8105   0.0314
  -3.250   0.2435   0.05847   0.05367  -0.0899   0.7987   0.0331
  -3.000   0.2882   0.05829   0.05331  -0.0959   0.7871   0.0337
  -2.750   0.2911   0.05215   0.04724  -0.0940   0.7785   0.0348
  -2.500   0.3132   0.04930   0.04429  -0.0952   0.7701   0.0366
  -2.250   0.3430   0.04726   0.04217  -0.0980   0.7603   0.0389
  -2.000   0.3759   0.04553   0.04030  -0.1010   0.7521   0.0418
  -1.750   0.4199   0.04541   0.03997  -0.1051   0.7432   0.0449
  -1.500   0.4705   0.04676   0.04104  -0.1099   0.7340   0.0458
  -1.250   0.4821   0.04118   0.03552  -0.1099   0.7279   0.0472
  -1.000   0.5090   0.03905   0.03333  -0.1116   0.7196   0.0499
  -0.750   0.5410   0.03766   0.03176  -0.1133   0.7132   0.0536
  -0.500   0.5866   0.03889   0.03275  -0.1164   0.7045   0.0579
  -0.250   0.6123   0.03591   0.02969  -0.1175   0.6989   0.0595
   0.000   0.6392   0.03408   0.02785  -0.1190   0.6909   0.0637
   0.250   0.6403   0.01490   0.00897  -0.1124   0.6721   0.0735
   0.500   0.6749   0.01523   0.00912  -0.1138   0.6651   0.0828
   0.750   0.7018   0.01349   0.00733  -0.1152   0.6593   0.0869
   1.000   0.7352   0.01357   0.00718  -0.1160   0.6537   0.0964
   1.250   0.7622   0.01251   0.00611  -0.1173   0.6472   0.1048
   1.500   0.7916   0.01181   0.00524  -0.1177   0.6422   0.1145
   1.750   0.8208   0.01173   0.00510  -0.1188   0.6353   0.1260
   2.000   0.8493   0.01130   0.00453  -0.1191   0.6298   0.1403
   2.250   0.8771   0.01113   0.00426  -0.1196   0.6239   0.1622
   2.500   0.9038   0.01080   0.00387  -0.1201   0.6176   0.2016
   2.750   0.9674   0.02654   0.01900  -0.1267   0.6218   0.2289
   3.000   0.9562   0.00995   0.00292  -0.1208   0.6058   0.3156
   3.250   0.9847   0.00967   0.00247  -0.1205   0.6007   0.3228
   3.500   1.0178   0.01088   0.00330  -0.1192   0.5944   0.1195
   3.750   1.0438   0.01073   0.00305  -0.1189   0.5883   0.1285
   4.000   1.0715   0.01049   0.00256  -0.1184   0.5836   0.1600
   4.250   1.0952   0.01104   0.00311  -0.1184   0.5759   0.1825
   4.500   1.1205   0.01067   0.00259  -0.1173   0.5713   0.1924
   4.750   1.1417   0.01139   0.00340  -0.1171   0.5627   0.2155
   5.000   1.1664   0.01116   0.00314  -0.1161   0.5577   0.2335
   5.250   1.1878   0.01194   0.00401  -0.1159   0.5492   0.2632
   5.500   1.2153   0.01151   0.00422  -0.1153   0.5439   1.0000
   5.750   1.2367   0.01250   0.00519  -0.1148   0.5352   1.0000
   6.000   1.2624   0.01242   0.00498  -0.1137   0.5294   1.0000
   6.250   1.2830   0.01343   0.00609  -0.1132   0.5202   1.0000
   6.500   1.3109   0.01301   0.00567  -0.1121   0.5143   1.0000
   6.750   1.3887   0.02815   0.02033  -0.1187   0.5157   1.0000
   7.000   1.4110   0.02864   0.02096  -0.1179   0.5059   1.0000
   7.250   1.4384   0.02822   0.02049  -0.1167   0.4987   1.0000
   7.500   1.4610   0.02848   0.02091  -0.1158   0.4878   1.0000
   7.750   1.4838   0.02864   0.02123  -0.1148   0.4767   1.0000
   8.000   1.5083   0.02845   0.02126  -0.1137   0.4657   1.0000
   8.250   1.5338   0.02800   0.02090  -0.1125   0.4541   1.0000
   8.500   1.5583   0.02757   0.02060  -0.1112   0.4408   1.0000
   8.750   1.5810   0.02725   0.02047  -0.1099   0.4251   1.0000
   9.000   1.6032   0.02688   0.02029  -0.1085   0.4072   1.0000
   9.250   1.6251   0.02622   0.01980  -0.1068   0.3856   1.0000
   9.500   1.6408   0.02589   0.01967  -0.1047   0.3508   1.0000
   9.750   1.6522   0.02621   0.01992  -0.1024   0.3037   1.0000
  10.000   1.6561   0.02769   0.02116  -0.0999   0.2452   1.0000
  10.250   1.6505   0.03023   0.02329  -0.0970   0.1899   1.0000
  10.500   1.6397   0.03314   0.02594  -0.0938   0.1476   1.0000
  10.750   1.6223   0.03633   0.02893  -0.0903   0.1174   1.0000
  11.000   1.6027   0.04036   0.03280  -0.0882   0.0920   1.0000
  11.250   1.5825   0.04514   0.03742  -0.0872   0.0737   1.0000
  11.500   1.5626   0.05040   0.04260  -0.0867   0.0587   1.0000
  11.750   1.5446   0.05570   0.04782  -0.0867   0.0511   1.0000
  12.000   1.5326   0.06044   0.05268  -0.0865   0.0440   1.0000
  12.250   1.5186   0.06539   0.05763  -0.0864   0.0406   1.0000
  12.500   1.5135   0.06926   0.06164  -0.0857   0.0370   1.0000
  12.750   1.5106   0.07281   0.06529  -0.0849   0.0341   1.0000
  13.000   1.5098   0.07607   0.06860  -0.0837   0.0317   1.0000
  13.250   1.5255   0.07755   0.07009  -0.0794   0.0294   1.0000
  13.500   1.5378   0.08023   0.07305  -0.0772   0.0284   1.0000
  13.750   1.5446   0.08391   0.07704  -0.0758   0.0278   1.0000
  14.000   1.5425   0.08849   0.08192  -0.0757   0.0273   1.0000
  14.250   1.5358   0.09356   0.08730  -0.0764   0.0269   1.0000
  14.500   1.5256   0.09903   0.09306  -0.0777   0.0265   1.0000
  14.750   1.5135   0.10490   0.09921  -0.0796   0.0263   1.0000
  15.000   1.4997   0.11126   0.10585  -0.0821   0.0263   1.0000
  15.250   1.4845   0.11805   0.11290  -0.0853   0.0264   1.0000
  15.500   1.4684   0.12533   0.12043  -0.0891   0.0266   1.0000
  15.750   1.4520   0.13306   0.12839  -0.0935   0.0269   1.0000
  16.000   1.4353   0.14135   0.13689  -0.0985   0.0276   1.0000
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