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EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 540 AIRFOIL (e540-il)
Reynolds number: 200,000
Max Cl/Cd: 54.02 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e540-il-200000.txt
Download as CSV file: xf-e540-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 540 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  -0.4175   0.10411   0.10079  -0.0620   1.0000   0.0469
 -11.500  -0.4283   0.09939   0.09613  -0.0634   1.0000   0.0474
 -11.250  -0.4488   0.09406   0.09090  -0.0647   1.0000   0.0480
  -8.750  -0.5420   0.03748   0.03107  -0.0792   0.9354   0.0227
  -8.500  -0.5096   0.03466   0.02799  -0.0807   0.9324   0.0213
  -8.250  -0.4756   0.03067   0.02360  -0.0826   0.9304   0.0207
  -8.000  -0.4319   0.02775   0.02034  -0.0856   0.9292   0.0204
  -7.750  -0.3788   0.02545   0.01779  -0.0896   0.9291   0.0211
  -7.500  -0.3340   0.02355   0.01582  -0.0919   0.9274   0.0244
  -7.250  -0.3050   0.02270   0.01494  -0.0924   0.9213   0.0279
  -7.000  -0.2713   0.02165   0.01382  -0.0936   0.9173   0.0303
  -6.750  -0.2560   0.02043   0.01260  -0.0921   0.9100   0.0349
  -6.500  -0.2402   0.01951   0.01169  -0.0908   0.9031   0.0465
  -6.250  -0.2377   0.01849   0.01081  -0.0872   0.8949   0.0743
  -6.000  -0.2461   0.01701   0.00992  -0.0824   0.8871   0.1703
  -5.750  -0.2664   0.01630   0.00960  -0.0748   0.8769   0.2468
  -5.500  -0.2882   0.01532   0.00916  -0.0670   0.8689   0.3571
  -5.250  -0.2869   0.01632   0.01166  -0.0593   0.8632   0.6481
  -5.000  -0.2740   0.01698   0.01212  -0.0563   0.8589   0.6908
  -4.750  -0.1959   0.02103   0.01601  -0.0598   0.8593   0.7111
  -4.500  -0.1317   0.02307   0.01785  -0.0634   0.8586   0.7223
  -4.250  -0.1096   0.02381   0.01848  -0.0616   0.8539   0.7338
  -4.000   0.0176   0.02601   0.02039  -0.0757   0.8579   0.7436
  -3.750   0.0693   0.02665   0.02091  -0.0789   0.8556   0.7527
  -3.500   0.0822   0.02678   0.02099  -0.0764   0.8503   0.7631
  -3.250   0.1260   0.02674   0.02084  -0.0792   0.8477   0.7671
  -3.000   0.1398   0.02666   0.02068  -0.0773   0.8439   0.7768
  -2.750   0.1802   0.02659   0.02054  -0.0796   0.8408   0.7804
  -2.500   0.1806   0.02669   0.02063  -0.0752   0.8352   0.7904
  -2.250   0.2277   0.02645   0.02031  -0.0788   0.8330   0.7937
  -2.000   0.2558   0.02631   0.02009  -0.0793   0.8302   0.7994
  -1.750   0.2758   0.02628   0.02005  -0.0782   0.8263   0.8067
  -1.500   0.3033   0.02620   0.01996  -0.0785   0.8225   0.8114
  -1.250   0.3074   0.02619   0.01992  -0.0748   0.8180   0.8189
  -1.000   0.3584   0.02587   0.01956  -0.0792   0.8163   0.8236
  -0.750   0.4658   0.02585   0.01954  -0.0916   0.8168   0.8776
  -0.500   0.3561   0.02599   0.01971  -0.0702   0.8061   0.8308
  -0.250   0.4136   0.02562   0.01931  -0.0758   0.8043   0.8367
   0.000   0.4392   0.02540   0.01907  -0.0759   0.8015   0.8399
   0.250   0.4404   0.02547   0.01918  -0.0718   0.7960   0.8406
   0.500   0.4465   0.02538   0.01910  -0.0685   0.7910   0.8420
   0.750   0.4564   0.02515   0.01886  -0.0658   0.7876   0.8435
   1.000   0.4365   0.02536   0.01911  -0.0577   0.7804   0.8440
   1.250   0.4104   0.02525   0.01899  -0.0483   0.7748   0.8450
   1.500   0.4429   0.02485   0.01858  -0.0496   0.7724   0.8465
   1.750   0.4179   0.02510   0.01889  -0.0405   0.7637   0.8475
   2.000   0.4529   0.02474   0.01853  -0.0422   0.7607   0.8485
   2.250   0.4943   0.02433   0.01813  -0.0450   0.7584   0.8496
   2.500   0.4525   0.02455   0.01839  -0.0330   0.7487   0.8505
   2.750   0.4871   0.02411   0.01797  -0.0345   0.7458   0.8516
   3.000   0.4713   0.02414   0.01804  -0.0273   0.7378   0.8528
   3.250   0.4968   0.02372   0.01763  -0.0274   0.7335   0.8534
   3.500   0.5374   0.02316   0.01709  -0.0299   0.7307   0.8543
   3.750   0.5270   0.02322   0.01721  -0.0239   0.7219   0.8560
   4.000   0.5650   0.02266   0.01667  -0.0260   0.7182   0.8564
   4.250   0.6117   0.02204   0.01605  -0.0297   0.7154   0.8568
   4.500   0.6093   0.02203   0.01613  -0.0251   0.7059   0.8582
   4.750   0.6554   0.02136   0.01548  -0.0286   0.7021   0.8590
   5.000   0.6656   0.02122   0.01542  -0.0259   0.6932   0.8600
   5.250   0.7091   0.02056   0.01479  -0.0288   0.6883   0.8603
   5.500   0.7232   0.02033   0.01467  -0.0265   0.6791   0.8611
   5.750   0.7680   0.01964   0.01400  -0.0295   0.6731   0.8615
   6.000   0.7807   0.01938   0.01385  -0.0269   0.6625   0.8625
   6.250   0.8035   0.01898   0.01353  -0.0260   0.6526   0.8636
   6.500   0.8322   0.01848   0.01310  -0.0261   0.6424   0.8648
   6.750   0.8561   0.01802   0.01270  -0.0254   0.6301   0.8659
   7.000   0.8715   0.01768   0.01244  -0.0232   0.6157   0.8671
   7.250   0.8821   0.01743   0.01228  -0.0203   0.5989   0.8684
   7.500   0.8928   0.01717   0.01208  -0.0173   0.5792   0.8697
   7.750   0.9046   0.01697   0.01190  -0.0147   0.5561   0.8711
   8.000   0.9156   0.01695   0.01182  -0.0119   0.5241   0.8726
   8.250   0.9246   0.01716   0.01191  -0.0090   0.4861   0.8743
   8.500   0.9271   0.01763   0.01219  -0.0049   0.4455   0.8759
   8.750   0.9272   0.01835   0.01272  -0.0010   0.4052   0.8775
   9.000   0.9259   0.01925   0.01344   0.0028   0.3655   0.8793
   9.250   0.9250   0.02029   0.01432   0.0062   0.3286   0.8812
   9.500   0.9244   0.02146   0.01533   0.0092   0.2928   0.8830
   9.750   0.9251   0.02273   0.01645   0.0117   0.2591   0.8849
  10.000   0.9275   0.02406   0.01764   0.0138   0.2265   0.8868
  10.250   0.9284   0.02538   0.01885   0.0161   0.1970   0.8889
  10.500   0.9294   0.02677   0.02013   0.0184   0.1692   0.8909
  10.750   0.9309   0.02828   0.02152   0.0203   0.1420   0.8929
  11.000   0.9330   0.02990   0.02302   0.0220   0.1187   0.8949
  11.250   0.9350   0.03161   0.02465   0.0236   0.0987   0.8970
  11.500   0.9359   0.03352   0.02646   0.0251   0.0836   0.8991
  11.750   0.9392   0.03537   0.02827   0.0263   0.0713   0.9011
  12.000   0.9451   0.03689   0.02984   0.0275   0.0617   0.9032
  12.250   0.9489   0.03864   0.03165   0.0288   0.0550   0.9055
  12.500   0.9537   0.04040   0.03342   0.0298   0.0492   0.9079
  12.750   0.9605   0.04215   0.03526   0.0307   0.0441   0.9107
  13.000   0.9682   0.04386   0.03704   0.0311   0.0396   0.9137
  13.250   0.9733   0.04594   0.03914   0.0320   0.0354   0.9164
  13.500   0.9807   0.04764   0.04101   0.0326   0.0317   0.9196
  13.750   0.9855   0.04971   0.04311   0.0330   0.0285   0.9229
  14.000   0.9934   0.05189   0.04539   0.0336   0.0256   0.9259
  14.250   0.9999   0.05400   0.04772   0.0338   0.0231   0.9297
  14.500   1.0049   0.05619   0.05002   0.0342   0.0212   0.9340
  14.750   1.0111   0.05895   0.05285   0.0348   0.0191   0.9376
  15.000   1.0152   0.06195   0.05610   0.0351   0.0183   0.9425
  15.250   1.0155   0.06482   0.05923   0.0346   0.0172   0.9504
  15.500   1.0175   0.06822   0.06289   0.0338   0.0166   0.9602
  15.750   1.0155   0.07165   0.06656   0.0328   0.0161   1.0000
  16.000   1.0145   0.07518   0.07020   0.0311   0.0149   1.0000
  16.250   1.0103   0.07954   0.07476   0.0295   0.0146   1.0000
  16.500   1.0050   0.08414   0.07953   0.0276   0.0143   1.0000
  16.750   0.9976   0.08914   0.08472   0.0254   0.0140   1.0000
  17.000   0.9847   0.09529   0.09113   0.0226   0.0141   1.0000
  17.250   0.9750   0.10097   0.09694   0.0196   0.0137   1.0000
  17.500   0.9598   0.10794   0.10414   0.0157   0.0137   1.0000
  17.750   0.9380   0.11659   0.11307   0.0107   0.0140   1.0000
  18.000   0.9115   0.12676   0.12351   0.0045   0.0144   1.0000
  18.250   0.8677   0.14204   0.13911  -0.0050   0.0153   1.0000
  18.500   0.7755   0.17617   0.17340  -0.0219   0.0205   1.0000
  18.750   0.7754   0.18222   0.17942  -0.0256   0.0199   1.0000
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