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EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 540 AIRFOIL (e540-il)
Reynolds number: 500,000
Max Cl/Cd: 85.34 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e540-il-500000.txt
Download as CSV file: xf-e540-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3184   0.08339   0.08138  -0.0783   0.9819   0.0191
 -11.750  -0.3549   0.06990   0.06781  -0.0864   0.9766   0.0182
 -11.500  -0.5205   0.06847   0.06602  -0.0820   0.9963   0.0162
 -11.250  -0.5293   0.06316   0.06058  -0.0857   0.9896   0.0164
 -11.000  -0.5392   0.05853   0.05580  -0.0877   0.9756   0.0165
 -10.750  -0.5425   0.05470   0.05182  -0.0897   0.9634   0.0167
 -10.500  -0.5393   0.05081   0.04774  -0.0926   0.9546   0.0171
 -10.250  -0.5285   0.04677   0.04344  -0.0966   0.9463   0.0175
 -10.000  -0.5133   0.04290   0.03928  -0.1003   0.9346   0.0182
  -9.750  -0.5019   0.03982   0.03587  -0.1014   0.9178   0.0191
  -9.500  -0.4805   0.01595   0.01080  -0.0946   0.8841   0.0106
  -9.250  -0.4848   0.02697   0.02151  -0.0964   0.8930   0.0097
  -9.000  -0.4490   0.02330   0.01742  -0.0980   0.8880   0.0088
  -8.750  -0.4144   0.02145   0.01531  -0.0988   0.8817   0.0084
  -8.500  -0.3836   0.02015   0.01382  -0.0991   0.8747   0.0084
  -8.250  -0.3599   0.01922   0.01275  -0.0984   0.8671   0.0085
  -8.000  -0.3400   0.01852   0.01193  -0.0974   0.8592   0.0084
  -7.750  -0.3234   0.01784   0.01116  -0.0958   0.8513   0.0088
  -7.500  -0.3072   0.01722   0.01044  -0.0943   0.8443   0.0094
  -7.250  -0.2904   0.01676   0.00991  -0.0927   0.8375   0.0101
  -7.000  -0.2804   0.01593   0.00898  -0.0903   0.8311   0.0107
  -6.750  -0.2680   0.01529   0.00830  -0.0881   0.8252   0.0121
  -6.500  -0.2528   0.01483   0.00778  -0.0864   0.8196   0.0139
  -6.250  -0.2397   0.01425   0.00714  -0.0843   0.8147   0.0198
  -6.000  -0.2333   0.01349   0.00651  -0.0810   0.8088   0.0437
  -5.750  -0.2271   0.01280   0.00600  -0.0779   0.8036   0.0842
  -5.500  -0.2247   0.01216   0.00556  -0.0740   0.7990   0.1339
  -5.250  -0.2300   0.01147   0.00517  -0.0687   0.7937   0.2010
  -5.000  -0.2342   0.01049   0.00465  -0.0637   0.7891   0.3104
  -4.750  -0.2426   0.00905   0.00391  -0.0582   0.7848   0.4792
  -4.500  -0.2346   0.00851   0.00412  -0.0546   0.7806   0.6619
  -4.250  -0.2072   0.00884   0.00436  -0.0544   0.7773   0.6900
  -4.000  -0.1786   0.00925   0.00468  -0.0544   0.7746   0.7038
  -3.750  -0.1476   0.00982   0.00522  -0.0546   0.7722   0.7125
  -3.500  -0.1203   0.01013   0.00548  -0.0544   0.7691   0.7204
  -3.250  -0.0901   0.01074   0.00611  -0.0542   0.7660   0.7264
  -3.000  -0.0607   0.01136   0.00670  -0.0540   0.7632   0.7349
  -2.750  -0.0252   0.01268   0.00805  -0.0538   0.7609   0.7413
  -2.500   0.0025   0.01299   0.00827  -0.0537   0.7585   0.7486
  -2.250   0.0304   0.01305   0.00832  -0.0538   0.7559   0.7496
  -2.000   0.0575   0.01307   0.00830  -0.0538   0.7528   0.7506
  -1.750   0.0849   0.01306   0.00826  -0.0539   0.7501   0.7519
  -1.500   0.1125   0.01302   0.00817  -0.0542   0.7476   0.7534
  -1.250   0.1403   0.01295   0.00804  -0.0546   0.7452   0.7552
  -1.000   0.1668   0.01279   0.00782  -0.0550   0.7427   0.7577
  -0.750   0.1912   0.01244   0.00741  -0.0554   0.7397   0.7612
  -0.500   0.2179   0.01234   0.00730  -0.0555   0.7368   0.7620
  -0.250   0.2455   0.01226   0.00719  -0.0557   0.7341   0.7628
   0.000   0.2739   0.01219   0.00710  -0.0562   0.7315   0.7635
   0.250   0.3024   0.01220   0.00708  -0.0566   0.7289   0.7643
   0.500   0.3279   0.01214   0.00704  -0.0564   0.7255   0.7652
   0.750   0.3549   0.01206   0.00696  -0.0566   0.7220   0.7660
   1.000   0.3830   0.01197   0.00686  -0.0571   0.7188   0.7669
   1.250   0.4122   0.01194   0.00678  -0.0577   0.7158   0.7679
   1.500   0.4378   0.01187   0.00675  -0.0577   0.7120   0.7692
   1.750   0.4645   0.01176   0.00664  -0.0579   0.7079   0.7704
   2.000   0.4930   0.01165   0.00651  -0.0584   0.7040   0.7715
   2.250   0.5219   0.01158   0.00641  -0.0591   0.7003   0.7725
   2.500   0.5474   0.01146   0.00633  -0.0591   0.6956   0.7738
   2.750   0.5756   0.01138   0.00623  -0.0596   0.6910   0.7751
   3.000   0.6048   0.01131   0.00613  -0.0602   0.6870   0.7758
   3.250   0.6288   0.01120   0.00611  -0.0597   0.6816   0.7765
   3.500   0.6556   0.01112   0.00604  -0.0598   0.6764   0.7771
   3.750   0.6831   0.01108   0.00601  -0.0600   0.6714   0.7778
   4.000   0.7075   0.01100   0.00601  -0.0596   0.6650   0.7785
   4.250   0.7349   0.01095   0.00595  -0.0597   0.6591   0.7793
   4.500   0.7586   0.01089   0.00597  -0.0591   0.6518   0.7801
   4.750   0.7849   0.01085   0.00594  -0.0591   0.6448   0.7810
   5.000   0.8077   0.01079   0.00596  -0.0583   0.6357   0.7821
   5.250   0.8316   0.01075   0.00595  -0.0577   0.6261   0.7832
   5.500   0.8549   0.01071   0.00593  -0.0571   0.6149   0.7841
   5.750   0.8770   0.01069   0.00594  -0.0562   0.6012   0.7852
   6.000   0.8980   0.01069   0.00598  -0.0551   0.5847   0.7862
   6.250   0.9167   0.01075   0.00601  -0.0535   0.5623   0.7873
   6.500   0.9311   0.01091   0.00608  -0.0511   0.5315   0.7883
   6.750   0.9388   0.01125   0.00623  -0.0475   0.4909   0.7894
   7.000   0.9384   0.01164   0.00645  -0.0422   0.4497   0.7905
   7.250   0.9385   0.01221   0.00685  -0.0373   0.4087   0.7917
   7.500   0.9388   0.01294   0.00739  -0.0326   0.3669   0.7930
   7.750   0.9417   0.01366   0.00796  -0.0287   0.3315   0.7943
   8.000   0.9468   0.01437   0.00856  -0.0253   0.2990   0.7955
   8.250   0.9511   0.01516   0.00922  -0.0219   0.2663   0.7968
   8.500   0.9556   0.01603   0.00994  -0.0188   0.2349   0.7981
   8.750   0.9618   0.01688   0.01067  -0.0161   0.2071   0.7994
   9.000   0.9684   0.01779   0.01146  -0.0136   0.1801   0.8006
   9.250   0.9761   0.01870   0.01227  -0.0114   0.1563   0.8019
   9.500   0.9836   0.01968   0.01314  -0.0093   0.1345   0.8030
   9.750   0.9914   0.02066   0.01403  -0.0073   0.1131   0.8041
  10.000   0.9985   0.02167   0.01498  -0.0052   0.0943   0.8053
  10.250   1.0062   0.02272   0.01596  -0.0033   0.0772   0.8067
  10.500   1.0133   0.02385   0.01705  -0.0015   0.0623   0.8080
  10.750   1.0210   0.02499   0.01814   0.0002   0.0503   0.8093
  11.000   1.0299   0.02610   0.01925   0.0017   0.0415   0.8106
  11.250   1.0377   0.02733   0.02047   0.0032   0.0350   0.8119
  11.500   1.0475   0.02845   0.02159   0.0044   0.0298   0.8133
  11.750   1.0539   0.02985   0.02304   0.0059   0.0263   0.8147
  12.000   1.0664   0.03086   0.02412   0.0067   0.0237   0.8160
  12.250   1.0745   0.03222   0.02548   0.0078   0.0207   0.8172
  12.500   1.0802   0.03375   0.02709   0.0091   0.0181   0.8185
  12.750   1.0900   0.03500   0.02842   0.0100   0.0161   0.8198
  13.000   1.0958   0.03660   0.03004   0.0110   0.0135   0.8212
  13.250   1.1008   0.03834   0.03190   0.0121   0.0116   0.8226
  13.500   1.1080   0.03995   0.03358   0.0129   0.0101   0.8242
  13.750   1.1114   0.04195   0.03565   0.0138   0.0092   0.8259
  14.000   1.1044   0.04499   0.03880   0.0151   0.0083   0.8276
  14.250   1.1062   0.04731   0.04124   0.0157   0.0080   0.8293
  14.500   1.1148   0.04906   0.04309   0.0159   0.0072   0.8309
  14.750   1.1205   0.05111   0.04522   0.0162   0.0064   0.8325
  15.000   1.1225   0.05355   0.04777   0.0164   0.0061   0.8341
  15.250   1.1215   0.05642   0.05074   0.0166   0.0057   0.8357
  15.500   1.1203   0.05943   0.05387   0.0166   0.0057   0.8373
  15.750   1.1176   0.06272   0.05728   0.0164   0.0055   0.8391
  16.000   1.0996   0.06803   0.06278   0.0163   0.0052   0.8403
  16.250   1.0969   0.07163   0.06652   0.0157   0.0051   0.8420
  16.500   1.0962   0.07513   0.07016   0.0148   0.0050   0.8438
  16.750   1.0949   0.07883   0.07400   0.0137   0.0049   0.8455
  17.000   1.0907   0.08291   0.07826   0.0126   0.0050   0.8472
  17.250   1.0864   0.08725   0.08276   0.0111   0.0048   0.8490
  17.500   1.0813   0.09179   0.08746   0.0094   0.0047   0.8509
  17.750   1.0748   0.09670   0.09254   0.0074   0.0047   0.8527
  18.000   1.0680   0.10183   0.09783   0.0050   0.0046   0.8547
  18.250   1.0580   0.10764   0.10381   0.0023   0.0046   0.8566
  18.500   1.0504   0.11323   0.10955  -0.0007   0.0045   0.8587
  18.750   1.0374   0.11990   0.11640  -0.0041   0.0045   0.8605
  19.000   1.0273   0.12616   0.12284  -0.0076   0.0045   0.8627
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