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EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 793 AIRFOIL (e793-il)
Reynolds number: 100,000
Max Cl/Cd: 43.26 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e793-il-100000.txt
Download as CSV file: xf-e793-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 793 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2978   0.11262   0.10780  -0.0409   1.0000   0.1476
  -9.750  -0.3208   0.10943   0.10475  -0.0426   1.0000   0.1492
  -9.500  -0.4196   0.07903   0.07443  -0.0582   1.0000   0.0797
  -9.250  -0.4213   0.07690   0.07238  -0.0559   1.0000   0.0788
  -9.000  -0.4424   0.07325   0.06884  -0.0547   1.0000   0.0774
  -8.750  -0.4952   0.06847   0.06418  -0.0538   1.0000   0.0758
  -8.500  -0.5570   0.06351   0.05924  -0.0548   1.0000   0.0742
  -8.250  -0.6384   0.05276   0.04738  -0.0603   1.0000   0.0690
  -8.000  -0.6131   0.04725   0.04149  -0.0656   0.9939   0.0684
  -7.750  -0.5808   0.04236   0.03603  -0.0711   0.9855   0.0681
  -7.500  -0.5451   0.03872   0.03170  -0.0758   0.9770   0.0689
  -7.250  -0.5054   0.03559   0.02837  -0.0801   0.9706   0.0714
  -7.000  -0.4690   0.03355   0.02615  -0.0828   0.9612   0.0738
  -6.750  -0.4305   0.03154   0.02386  -0.0855   0.9528   0.0761
  -6.250  -0.3525   0.02810   0.02015  -0.0904   0.9358   0.0846
  -6.000  -0.3062   0.02655   0.01855  -0.0939   0.9299   0.0944
  -5.750  -0.2734   0.02523   0.01730  -0.0951   0.9188   0.1070
  -5.500  -0.2258   0.02337   0.01572  -0.0993   0.9136   0.1493
  -5.250  -0.1935   0.02227   0.01496  -0.1009   0.9019   0.2124
  -5.000  -0.1501   0.02200   0.01483  -0.1039   0.8938   0.2701
  -4.750  -0.1088   0.02215   0.01501  -0.1061   0.8847   0.3145
  -4.500  -0.0650   0.02209   0.01493  -0.1084   0.8771   0.3476
  -4.250  -0.0249   0.02192   0.01474  -0.1101   0.8679   0.3738
  -4.000   0.0133   0.02172   0.01447  -0.1114   0.8586   0.3972
  -3.750   0.0541   0.02145   0.01421  -0.1129   0.8500   0.4184
  -3.500   0.0869   0.02127   0.01400  -0.1132   0.8385   0.4370
  -3.250   0.1297   0.02087   0.01353  -0.1151   0.8309   0.4566
  -3.000   0.1581   0.02072   0.01332  -0.1147   0.8176   0.4723
  -2.750   0.1892   0.02052   0.01304  -0.1148   0.8058   0.4882
  -2.500   0.2264   0.02018   0.01259  -0.1159   0.7965   0.5047
  -2.250   0.2529   0.02009   0.01242  -0.1153   0.7828   0.5197
  -2.000   0.2808   0.02000   0.01226  -0.1149   0.7704   0.5344
  -1.750   0.3122   0.01982   0.01202  -0.1149   0.7601   0.5485
  -1.500   0.3391   0.01973   0.01189  -0.1143   0.7478   0.5624
  -1.250   0.3651   0.01970   0.01182  -0.1137   0.7356   0.5768
  -1.000   0.3948   0.01961   0.01163  -0.1136   0.7254   0.5924
  -0.750   0.4215   0.01957   0.01154  -0.1131   0.7139   0.6080
  -0.500   0.4469   0.01962   0.01155  -0.1124   0.7025   0.6240
  -0.250   0.4774   0.01953   0.01136  -0.1124   0.6937   0.6411
   0.000   0.5001   0.01962   0.01149  -0.1112   0.6818   0.6580
   0.250   0.5256   0.01967   0.01153  -0.1105   0.6719   0.6758
   0.500   0.5517   0.01967   0.01151  -0.1097   0.6625   0.6944
   0.750   0.5741   0.01978   0.01168  -0.1084   0.6522   0.7138
   1.000   0.6012   0.01976   0.01160  -0.1077   0.6441   0.7354
   1.250   0.6217   0.01993   0.01184  -0.1062   0.6337   0.7590
   1.500   0.6475   0.01988   0.01174  -0.1051   0.6265   0.7837
   1.750   0.6652   0.02005   0.01203  -0.1030   0.6163   0.8119
   2.000   0.6886   0.01997   0.01190  -0.1014   0.6095   0.8442
   2.250   0.7007   0.02006   0.01216  -0.0980   0.6001   0.8826
   2.500   0.7327   0.01985   0.01192  -0.0981   0.5930   0.9412
   2.750   0.7748   0.02017   0.01223  -0.1021   0.5823   1.0000
   3.000   0.8127   0.02040   0.01222  -0.1045   0.5755   1.0000
   3.250   0.8367   0.02095   0.01278  -0.1046   0.5657   1.0000
   3.500   0.8705   0.02119   0.01282  -0.1058   0.5591   1.0000
   3.750   0.8924   0.02180   0.01347  -0.1053   0.5500   1.0000
   4.000   0.9236   0.02208   0.01362  -0.1059   0.5433   1.0000
   4.250   0.9460   0.02269   0.01425  -0.1053   0.5351   1.0000
   4.500   0.9745   0.02304   0.01452  -0.1054   0.5280   1.0000
   4.750   0.9997   0.02359   0.01507  -0.1052   0.5210   1.0000
   5.000   1.0237   0.02411   0.01560  -0.1047   0.5133   1.0000
   5.250   1.0560   0.02441   0.01576  -0.1054   0.5076   1.0000
   5.500   1.0724   0.02523   0.01675  -0.1039   0.4992   1.0000
   5.750   1.1025   0.02555   0.01698  -0.1042   0.4932   1.0000
   6.000   1.1222   0.02634   0.01786  -0.1032   0.4860   1.0000
   6.250   1.1470   0.02684   0.01838  -0.1028   0.4790   1.0000
   6.500   1.1772   0.02726   0.01872  -0.1032   0.4736   1.0000
   6.750   1.1911   0.02822   0.01987  -0.1014   0.4656   1.0000
   7.000   1.2218   0.02850   0.02009  -0.1017   0.4599   1.0000
   7.250   1.2383   0.02946   0.02118  -0.1003   0.4529   1.0000
   7.500   1.2610   0.03004   0.02181  -0.0997   0.4461   1.0000
   7.750   1.2933   0.03032   0.02201  -0.1002   0.4406   1.0000
   8.000   1.3014   0.03153   0.02345  -0.0977   0.4326   1.0000
   8.250   1.3338   0.03165   0.02350  -0.0982   0.4267   1.0000
   8.500   1.3456   0.03277   0.02479  -0.0962   0.4195   1.0000
   8.750   1.3684   0.03324   0.02532  -0.0955   0.4126   1.0000
   9.000   1.3963   0.03362   0.02568  -0.0955   0.4065   1.0000
   9.250   1.4036   0.03477   0.02704  -0.0929   0.3988   1.0000
   9.500   1.4436   0.03448   0.02661  -0.0942   0.3927   1.0000
   9.750   1.4414   0.03606   0.02848  -0.0905   0.3850   1.0000
  10.000   1.4739   0.03593   0.02830  -0.0909   0.3780   1.0000
  10.250   1.4817   0.03705   0.02958  -0.0884   0.3708   1.0000
  10.500   1.5034   0.03732   0.02990  -0.0874   0.3633   1.0000
  10.750   1.5217   0.03789   0.03053  -0.0862   0.3562   1.0000
  11.000   1.5315   0.03862   0.03139  -0.0838   0.3485   1.0000
  11.250   1.5582   0.03873   0.03148  -0.0835   0.3411   1.0000
  11.500   1.5563   0.03989   0.03283  -0.0798   0.3335   1.0000
  11.750   1.5877   0.03970   0.03258  -0.0799   0.3256   1.0000
  12.000   1.5730   0.04121   0.03431  -0.0747   0.3186   1.0000
  12.250   1.6075   0.04079   0.03379  -0.0752   0.3101   1.0000
  12.500   1.5853   0.04272   0.03596  -0.0695   0.3035   1.0000
  12.750   1.6185   0.04222   0.03536  -0.0697   0.2945   1.0000
  13.000   1.5923   0.04460   0.03799  -0.0645   0.2881   1.0000
  13.250   1.2067   0.09140   0.08537  -0.0654   0.2784   1.0000
  13.500   1.2719   0.08356   0.07765  -0.0616   0.2760   1.0000
  13.750   1.6159   0.04701   0.04046  -0.0590   0.2632   1.0000
  14.000   1.5896   0.05034   0.04401  -0.0558   0.2566   1.0000
  14.250   1.6056   0.05076   0.04436  -0.0548   0.2475   1.0000
  14.500   1.5838   0.05424   0.04803  -0.0528   0.2406   1.0000
  14.750   1.5905   0.05557   0.04936  -0.0517   0.2320   1.0000
  15.000   1.5770   0.05881   0.05271  -0.0507   0.2245   1.0000
  15.250   1.5730   0.06141   0.05535  -0.0499   0.2168   1.0000
  15.500   1.5690   0.06402   0.05800  -0.0494   0.2087   1.0000
  15.750   1.5544   0.06811   0.06221  -0.0493   0.2020   1.0000
  16.000   1.5558   0.07037   0.06447  -0.0491   0.1938   1.0000
  16.250   1.5365   0.07548   0.06972  -0.0497   0.1877   1.0000
  16.500   1.5264   0.07954   0.07386  -0.0503   0.1808   1.0000
  16.750   1.5212   0.08318   0.07754  -0.0508   0.1741   1.0000
  17.000   1.4832   0.09180   0.08640  -0.0536   0.1696   1.0000
  17.250   1.5105   0.09074   0.08518  -0.0523   0.1610   1.0000
  17.500   1.4554   0.10266   0.09744  -0.0572   0.1583   1.0000
  17.750   1.5074   0.09751   0.09202  -0.0538   0.1484   1.0000
  18.000   1.4490   0.11041   0.10528  -0.0597   0.1465   1.0000
  18.250   1.0583   0.20708   0.20187  -0.1161   0.1451   1.0000
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