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EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 543 AIRFOIL (e543-il)
Reynolds number: 200,000
Max Cl/Cd: 56.58 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e543-il-200000.txt
Download as CSV file: xf-e543-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 543 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3336   0.09521   0.09221  -0.0594   1.0000   0.0606
 -11.250  -0.3649   0.08749   0.08456  -0.0630   1.0000   0.0617
 -11.000  -0.3956   0.08355   0.08070  -0.0622   0.9992   0.0614
 -10.750  -0.4238   0.07452   0.07157  -0.0684   0.9959   0.0614
  -9.500  -0.5863   0.05981   0.05590  -0.0699   0.9694   0.0602
  -8.750  -0.5779   0.03860   0.03256  -0.0673   0.9432   0.0327
  -8.500  -0.5510   0.03302   0.02619  -0.0665   0.9366   0.0253
  -8.250  -0.5123   0.02958   0.02240  -0.0687   0.9324   0.0242
  -8.000  -0.4624   0.02665   0.01911  -0.0722   0.9303   0.0238
  -7.750  -0.4050   0.02452   0.01678  -0.0767   0.9293   0.0245
  -7.500  -0.3534   0.02301   0.01516  -0.0803   0.9268   0.0258
  -7.250  -0.3196   0.02178   0.01399  -0.0815   0.9176   0.0285
  -7.000  -0.2860   0.02070   0.01290  -0.0833   0.9098   0.0337
  -6.750  -0.2662   0.01982   0.01199  -0.0826   0.8976   0.0390
  -6.500  -0.2526   0.01890   0.01110  -0.0808   0.8855   0.0498
  -6.250  -0.2456   0.01781   0.01014  -0.0780   0.8743   0.0784
  -6.000  -0.2495   0.01652   0.00929  -0.0736   0.8627   0.1508
  -5.750  -0.2649   0.01549   0.00871  -0.0670   0.8501   0.2392
  -5.500  -0.2847   0.01453   0.00823  -0.0594   0.8395   0.3403
  -5.000  -0.2706   0.01582   0.01096  -0.0486   0.8246   0.6848
  -4.750  -0.2387   0.01764   0.01262  -0.0471   0.8182   0.7097
  -4.500  -0.1583   0.02093   0.01570  -0.0517   0.8155   0.7200
  -4.250  -0.1116   0.02225   0.01684  -0.0531   0.8110   0.7307
  -4.000  -0.0360   0.02380   0.01821  -0.0593   0.8069   0.7378
  -3.750   0.0383   0.02533   0.01956  -0.0651   0.8029   0.7504
  -3.500   0.0656   0.02557   0.01966  -0.0647   0.7976   0.7620
  -3.250   0.1079   0.02569   0.01967  -0.0670   0.7919   0.7665
  -3.000   0.1165   0.02561   0.01953  -0.0640   0.7854   0.7771
  -2.750   0.1620   0.02552   0.01931  -0.0670   0.7814   0.7803
  -2.500   0.1624   0.02553   0.01929  -0.0627   0.7750   0.7904
  -2.250   0.2032   0.02531   0.01898  -0.0651   0.7699   0.7939
  -2.000   0.2422   0.02513   0.01870  -0.0672   0.7657   0.7977
  -1.750   0.2344   0.02514   0.01870  -0.0615   0.7600   0.8075
  -1.500   0.2813   0.02488   0.01839  -0.0650   0.7554   0.8102
  -1.250   0.3159   0.02468   0.01812  -0.0665   0.7511   0.8141
  -1.000   0.3329   0.02456   0.01792  -0.0651   0.7471   0.8192
  -0.750   0.3483   0.02442   0.01782  -0.0633   0.7416   0.8251
  -0.500   0.4658   0.02509   0.01846  -0.0766   0.7386   0.8855
  -0.250   0.5079   0.02429   0.01762  -0.0798   0.7346   0.8899
   0.000   0.5286   0.02440   0.01769  -0.0790   0.7310   0.9008
   0.250   0.5634   0.02375   0.01709  -0.0810   0.7258   0.9052
   0.500   0.5798   0.02395   0.01729  -0.0793   0.7210   0.9154
   0.750   0.6185   0.02317   0.01649  -0.0821   0.7173   0.9190
   1.000   0.5016   0.02320   0.01652  -0.0593   0.7112   0.8451
   1.250   0.5152   0.02304   0.01639  -0.0573   0.7062   0.8465
   1.500   0.5307   0.02283   0.01615  -0.0556   0.7021   0.8475
   1.750   0.5452   0.02268   0.01598  -0.0537   0.6984   0.8491
   2.000   0.5414   0.02260   0.01600  -0.0485   0.6925   0.8496
   2.250   0.5344   0.02244   0.01583  -0.0425   0.6877   0.8511
   2.500   0.5367   0.02217   0.01552  -0.0384   0.6840   0.8520
   2.750   0.5207   0.02201   0.01542  -0.0312   0.6783   0.8539
   3.000   0.5397   0.02178   0.01523  -0.0301   0.6730   0.8545
   3.250   0.5694   0.02153   0.01497  -0.0307   0.6689   0.8553
   3.500   0.5898   0.02146   0.01494  -0.0297   0.6638   0.8566
   3.750   0.6033   0.02131   0.01484  -0.0276   0.6578   0.8575
   4.000   0.6289   0.02104   0.01458  -0.0276   0.6533   0.8582
   4.250   0.6455   0.02091   0.01449  -0.0261   0.6479   0.8590
   4.500   0.6611   0.02077   0.01441  -0.0243   0.6414   0.8605
   4.750   0.6903   0.02050   0.01412  -0.0249   0.6366   0.8616
   5.000   0.7035   0.02039   0.01411  -0.0229   0.6299   0.8627
   5.250   0.7263   0.02015   0.01390  -0.0224   0.6234   0.8636
   5.500   0.7549   0.01990   0.01365  -0.0230   0.6176   0.8645
   5.750   0.7703   0.01975   0.01360  -0.0213   0.6094   0.8657
   6.000   0.8053   0.01944   0.01325  -0.0230   0.6033   0.8669
   6.250   0.8182   0.01934   0.01329  -0.0209   0.5940   0.8685
   6.500   0.8511   0.01904   0.01298  -0.0222   0.5867   0.8692
   6.750   0.8652   0.01886   0.01294  -0.0199   0.5769   0.8702
   7.000   0.8888   0.01863   0.01275  -0.0194   0.5678   0.8711
   7.250   0.9112   0.01837   0.01256  -0.0185   0.5576   0.8722
   7.500   0.9266   0.01820   0.01249  -0.0165   0.5457   0.8735
   7.750   0.9443   0.01800   0.01237  -0.0149   0.5332   0.8749
   8.000   0.9609   0.01783   0.01227  -0.0130   0.5196   0.8767
   8.250   0.9749   0.01771   0.01221  -0.0108   0.5039   0.8787
   8.500   0.9867   0.01763   0.01218  -0.0083   0.4860   0.8804
   8.750   0.9958   0.01760   0.01217  -0.0054   0.4662   0.8821
   9.000   1.0049   0.01778   0.01232  -0.0027   0.4430   0.8839
   9.250   1.0094   0.01809   0.01257   0.0008   0.4169   0.8857
   9.500   1.0115   0.01860   0.01302   0.0045   0.3890   0.8877
   9.750   1.0120   0.01931   0.01363   0.0081   0.3608   0.8900
  10.000   1.0113   0.02021   0.01443   0.0115   0.3333   0.8929
  10.250   1.0103   0.02131   0.01541   0.0145   0.3074   0.8958
  10.500   1.0104   0.02253   0.01655   0.0170   0.2807   0.8984
  10.750   1.0094   0.02382   0.01778   0.0195   0.2572   0.9007
  11.000   1.0073   0.02521   0.01911   0.0221   0.2345   0.9034
  11.250   1.0057   0.02672   0.02056   0.0243   0.2136   0.9064
  11.500   1.0060   0.02830   0.02209   0.0260   0.1928   0.9095
  11.750   1.0057   0.03005   0.02377   0.0275   0.1738   0.9127
  12.000   1.0048   0.03187   0.02553   0.0290   0.1567   0.9158
  12.250   1.0053   0.03364   0.02729   0.0304   0.1404   0.9195
  12.500   1.0060   0.03553   0.02917   0.0314   0.1251   0.9239
  12.750   1.0068   0.03757   0.03118   0.0323   0.1116   0.9285
  13.000   1.0070   0.03967   0.03326   0.0331   0.0998   0.9332
  13.250   1.0073   0.04191   0.03548   0.0337   0.0890   0.9388
  13.500   1.0113   0.04404   0.03768   0.0338   0.0792   0.9453
  13.750   1.0164   0.04637   0.04007   0.0334   0.0704   0.9535
  14.000   1.0219   0.04900   0.04272   0.0324   0.0631   0.9649
  14.250   1.0247   0.05143   0.04518   0.0317   0.0570   1.0000
  14.500   1.0306   0.05390   0.04773   0.0311   0.0515   1.0000
  14.750   1.0333   0.05662   0.05038   0.0305   0.0471   1.0000
  15.000   1.0400   0.05915   0.05306   0.0297   0.0430   1.0000
  15.250   1.0438   0.06185   0.05572   0.0289   0.0397   1.0000
  15.500   1.0487   0.06464   0.05864   0.0281   0.0362   1.0000
  15.750   1.0523   0.06749   0.06149   0.0271   0.0334   1.0000
  16.000   1.0561   0.07040   0.06452   0.0264   0.0307   1.0000
  16.250   1.0588   0.07350   0.06767   0.0251   0.0283   1.0000
  16.500   1.0611   0.07663   0.07086   0.0243   0.0260   1.0000
  16.750   1.0616   0.08016   0.07451   0.0228   0.0239   1.0000
  17.000   1.0658   0.08296   0.07726   0.0221   0.0221   1.0000
  17.250   1.0633   0.08708   0.08161   0.0204   0.0207   1.0000
  17.500   1.0621   0.09095   0.08554   0.0185   0.0192   1.0000
  17.750   1.0650   0.09407   0.08868   0.0176   0.0180   1.0000
  18.000   1.0612   0.09853   0.09338   0.0159   0.0171   1.0000
  18.250   1.0602   0.10251   0.09752   0.0142   0.0166   1.0000
  18.500   1.0574   0.10680   0.10189   0.0120   0.0157   1.0000
  18.750   1.0633   0.10943   0.10447   0.0112   0.0149   1.0000
  19.000   1.0511   0.11558   0.11091   0.0079   0.0146   1.0000
  19.250   1.0380   0.12208   0.11766   0.0043   0.0142   1.0000
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