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EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 541 AIRFOIL (e541-il)
Reynolds number: 200,000
Max Cl/Cd: 46.82 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e541-il-200000.txt
Download as CSV file: xf-e541-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 541 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2492   0.09217   0.08903  -0.0892   0.9699   0.0534
 -11.500  -0.2632   0.08399   0.08086  -0.0955   0.9679   0.0548
 -11.250  -0.2864   0.07501   0.07183  -0.1020   0.9644   0.0550
 -11.000  -0.3163   0.06744   0.06414  -0.1068   0.9611   0.0552
 -10.750  -0.3429   0.06150   0.05803  -0.1095   0.9578   0.0555
 -10.500  -0.3701   0.05724   0.05355  -0.1104   0.9527   0.0559
 -10.250  -0.3921   0.05448   0.05056  -0.1095   0.9453   0.0562
 -10.000  -0.4182   0.05301   0.04885  -0.1059   0.9359   0.0565
  -8.500  -0.4678   0.04175   0.03559  -0.0893   0.9124   0.0327
  -8.250  -0.4635   0.03621   0.02940  -0.0848   0.9065   0.0235
  -8.000  -0.4360   0.03151   0.02442  -0.0855   0.9042   0.0218
  -7.750  -0.4025   0.02853   0.02107  -0.0865   0.9024   0.0211
  -7.500  -0.3450   0.02565   0.01785  -0.0915   0.9026   0.0210
  -7.250  -0.2948   0.02391   0.01595  -0.0947   0.9022   0.0221
  -7.000  -0.2589   0.02249   0.01449  -0.0960   0.9007   0.0256
  -6.750  -0.2376   0.02193   0.01393  -0.0953   0.8976   0.0289
  -6.500  -0.2230   0.02145   0.01339  -0.0931   0.8928   0.0326
  -6.250  -0.2138   0.02050   0.01246  -0.0903   0.8886   0.0410
  -6.000  -0.2050   0.01958   0.01163  -0.0875   0.8854   0.0623
  -5.750  -0.2158   0.01881   0.01134  -0.0815   0.8797   0.1289
  -5.500  -0.2313   0.01791   0.01101  -0.0748   0.8741   0.2392
  -5.250  -0.2541   0.01745   0.01096  -0.0665   0.8687   0.3249
  -5.000  -0.2829   0.01753   0.01134  -0.0567   0.8616   0.3843
  -4.750  -0.2521   0.02028   0.01557  -0.0519   0.8604   0.7147
  -4.500  -0.1742   0.02361   0.01864  -0.0568   0.8613   0.7452
  -4.250  -0.0639   0.02572   0.02042  -0.0688   0.8645   0.7581
  -4.000  -0.0167   0.02654   0.02109  -0.0714   0.8632   0.7683
  -3.750   0.0587   0.02770   0.02208  -0.0781   0.8638   0.7831
  -3.500   0.0965   0.02812   0.02240  -0.0795   0.8620   0.7954
  -3.250   0.1169   0.02839   0.02259  -0.0784   0.8595   0.8059
  -3.000   0.1642   0.02813   0.02224  -0.0821   0.8585   0.8104
  -2.750   0.1795   0.02837   0.02240  -0.0802   0.8561   0.8214
  -2.500   0.2226   0.02819   0.02217  -0.0833   0.8538   0.8256
  -2.250   0.2342   0.02858   0.02255  -0.0808   0.8500   0.8364
  -2.000   0.2776   0.02834   0.02225  -0.0840   0.8483   0.8430
  -1.750   0.3617   0.02808   0.02196  -0.0931   0.8491   0.8807
  -1.500   0.3898   0.02796   0.02181  -0.0937   0.8467   0.8925
  -1.250   0.4109   0.02821   0.02204  -0.0930   0.8443   0.9040
  -1.000   0.4548   0.02719   0.02099  -0.0969   0.8430   0.9077
  -0.750   0.4677   0.02764   0.02147  -0.0949   0.8389   0.9187
  -0.500   0.5012   0.02709   0.02094  -0.0970   0.8357   0.9234
  -0.250   0.5207   0.02723   0.02108  -0.0961   0.8325   0.9331
   0.000   0.5590   0.02648   0.02033  -0.0990   0.8305   0.9371
   0.250   0.5827   0.02655   0.02040  -0.0987   0.8283   0.9462
   0.500   0.6082   0.02628   0.02021  -0.0995   0.8228   0.9517
   0.750   0.6320   0.02619   0.02013  -0.0995   0.8188   0.9595
   1.000   0.6696   0.02547   0.01945  -0.1021   0.8162   0.9640
   1.250   0.6998   0.02515   0.01914  -0.1030   0.8136   0.9708
   1.500   0.7254   0.02487   0.01894  -0.1037   0.8063   0.9771
   1.750   0.7599   0.02427   0.01838  -0.1055   0.8027   0.9836
   2.000   0.7995   0.02330   0.01744  -0.1082   0.7998   0.9868
   3.000   0.6159   0.02807   0.02223  -0.0543   0.7638   0.9162
   3.250   0.6502   0.02729   0.02148  -0.0555   0.7606   0.9162
   3.500   0.6916   0.02633   0.02055  -0.0580   0.7583   0.9163
   3.750   0.6828   0.02655   0.02084  -0.0517   0.7484   0.9143
   4.000   0.7235   0.02557   0.01992  -0.0539   0.7454   0.9147
   4.250   0.7141   0.02563   0.02003  -0.0474   0.7365   0.9122
   4.500   0.4309   0.02756   0.02168   0.0095   0.7096   0.9100
   4.750   0.5021   0.02639   0.02061   0.0022   0.7103   0.9096
   5.000   0.5813   0.02538   0.01973  -0.0070   0.7095   0.9094
   5.250   0.8146   0.02271   0.01735  -0.0448   0.7133   0.9114
   5.500   0.8006   0.02249   0.01718  -0.0369   0.7042   0.9110
   5.750   0.7012   0.02269   0.01728  -0.0129   0.6942   0.9108
   6.000   0.7809   0.02141   0.01614  -0.0222   0.6889   0.9108
   6.250   0.7190   0.02124   0.01596  -0.0056   0.6787   0.9115
   6.500   0.7692   0.02020   0.01500  -0.0093   0.6711   0.9116
   6.750   0.7642   0.01957   0.01441  -0.0031   0.6604   0.9128
   7.000   0.7489   0.01914   0.01403   0.0047   0.6483   0.9144
   7.250   0.7563   0.01866   0.01361   0.0083   0.6342   0.9153
   7.500   0.7759   0.01812   0.01313   0.0097   0.6173   0.9159
   7.750   0.7814   0.01804   0.01311   0.0131   0.5950   0.9169
   8.000   0.8018   0.01770   0.01276   0.0143   0.5659   0.9177
   8.250   0.8202   0.01752   0.01245   0.0159   0.5274   0.9188
   8.500   0.8306   0.01775   0.01247   0.0186   0.4839   0.9201
   8.750   0.8344   0.01833   0.01284   0.0218   0.4410   0.9213
   9.000   0.8354   0.01913   0.01345   0.0251   0.4002   0.9226
   9.250   0.8347   0.02011   0.01423   0.0283   0.3597   0.9240
   9.500   0.8351   0.02118   0.01516   0.0311   0.3209   0.9254
   9.750   0.8369   0.02232   0.01615   0.0335   0.2835   0.9269
  10.000   0.8399   0.02353   0.01720   0.0355   0.2493   0.9283
  10.250   0.8440   0.02477   0.01831   0.0373   0.2160   0.9300
  10.500   0.8485   0.02611   0.01951   0.0389   0.1830   0.9316
  10.750   0.8517   0.02743   0.02069   0.0407   0.1534   0.9330
  11.000   0.8556   0.02884   0.02197   0.0423   0.1263   0.9344
  11.250   0.8601   0.03031   0.02334   0.0438   0.1034   0.9359
  11.500   0.8632   0.03194   0.02487   0.0453   0.0860   0.9375
  11.750   0.8667   0.03366   0.02653   0.0466   0.0723   0.9392
  12.000   0.8730   0.03528   0.02815   0.0476   0.0615   0.9408
  12.250   0.8804   0.03691   0.02987   0.0485   0.0537   0.9425
  12.500   0.8853   0.03880   0.03171   0.0494   0.0477   0.9440
  12.750   0.8972   0.04018   0.03324   0.0498   0.0426   0.9457
  13.000   0.9040   0.04186   0.03493   0.0504   0.0380   0.9477
  13.250   0.9126   0.04357   0.03676   0.0512   0.0338   0.9499
  13.500   0.9216   0.04525   0.03854   0.0516   0.0302   0.9525
  13.750   0.9280   0.04750   0.04081   0.0523   0.0261   0.9545
  14.000   0.9362   0.04937   0.04287   0.0523   0.0233   0.9571
  14.250   0.9445   0.05141   0.04503   0.0524   0.0212   0.9594
  14.500   0.9525   0.05387   0.04754   0.0527   0.0192   0.9613
  14.750   0.9612   0.05686   0.05078   0.0532   0.0182   0.9631
  15.000   0.9634   0.05966   0.05386   0.0530   0.0171   0.9663
  15.250   0.9652   0.06276   0.05719   0.0525   0.0162   0.9696
  15.500   0.9677   0.06559   0.06020   0.0509   0.0150   0.9738
  15.750   0.9678   0.06902   0.06378   0.0493   0.0141   0.9787
  16.000   0.9645   0.07264   0.06759   0.0483   0.0138   1.0000
  16.250   0.9595   0.07696   0.07210   0.0469   0.0135   1.0000
  16.500   0.9522   0.08175   0.07708   0.0452   0.0133   1.0000
  16.750   0.9415   0.08720   0.08273   0.0430   0.0131   1.0000
  17.000   0.9269   0.09346   0.08923   0.0402   0.0130   1.0000
  17.250   0.9147   0.09962   0.09561   0.0368   0.0131   1.0000
  17.500   0.8971   0.10701   0.10322   0.0327   0.0130   1.0000
  17.750   0.8803   0.11477   0.11120   0.0278   0.0131   1.0000
  18.000   0.8553   0.12498   0.12171   0.0211   0.0136   1.0000
  18.250   0.7611   0.15476   0.15193   0.0042   0.0168   1.0000
  18.500   0.7392   0.16648   0.16361  -0.0016   0.0185   1.0000
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