Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 542 AIRFOIL (e542-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.97 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e542-il-1000000-n5.txt
Download as CSV file: xf-e542-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 542 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.7764   0.07239   0.06998  -0.0657   1.0000   0.0020
 -15.500  -0.8072   0.06332   0.06071  -0.0706   1.0000   0.0020
 -15.250  -0.8320   0.05675   0.05396  -0.0728   1.0000   0.0020
 -15.000  -0.8483   0.05214   0.04919  -0.0734   1.0000   0.0020
 -14.750  -0.8727   0.04718   0.04402  -0.0729   1.0000   0.0020
 -14.500  -0.8786   0.04450   0.04121  -0.0718   1.0000   0.0020
 -14.250  -0.8848   0.04197   0.03855  -0.0704   1.0000   0.0020
 -14.000  -0.8958   0.03913   0.03553  -0.0683   1.0000   0.0020
 -13.750  -0.8933   0.03759   0.03390  -0.0668   1.0000   0.0020
 -13.500  -0.8982   0.03545   0.03162  -0.0644   1.0000   0.0020
 -13.000  -0.8954   0.02979   0.02548  -0.0631   0.9968   0.0022
 -12.750  -0.8839   0.02873   0.02436  -0.0619   0.9874   0.0023
 -12.500  -0.8672   0.02715   0.02264  -0.0622   0.9621   0.0024
 -12.250  -0.8255   0.02563   0.02099  -0.0675   0.9494   0.0024
 -12.000  -0.7755   0.02413   0.01934  -0.0744   0.9392   0.0025
 -11.750  -0.7222   0.02266   0.01769  -0.0820   0.9262   0.0026
 -11.500  -0.6733   0.02180   0.01666  -0.0881   0.8981   0.0028
 -11.250  -0.6535   0.02104   0.01568  -0.0879   0.8703   0.0029
 -11.000  -0.6413   0.02016   0.01459  -0.0860   0.8480   0.0028
 -10.750  -0.6254   0.01966   0.01397  -0.0846   0.8312   0.0029
 -10.500  -0.6103   0.01907   0.01327  -0.0831   0.8177   0.0029
 -10.250  -0.5928   0.01866   0.01276  -0.0819   0.8060   0.0031
  -9.750  -0.5594   0.01764   0.01155  -0.0792   0.7842   0.0031
  -9.500  -0.5425   0.01714   0.01096  -0.0778   0.7742   0.0033
  -9.250  -0.5265   0.01656   0.01029  -0.0763   0.7648   0.0032
  -9.000  -0.5063   0.01631   0.00998  -0.0754   0.7568   0.0033
  -8.750  -0.4887   0.01585   0.00944  -0.0741   0.7487   0.0034
  -8.500  -0.4714   0.01537   0.00889  -0.0727   0.7416   0.0034
  -8.250  -0.4513   0.01508   0.00855  -0.0717   0.7343   0.0035
  -8.000  -0.4340   0.01464   0.00804  -0.0703   0.7273   0.0036
  -7.750  -0.4153   0.01426   0.00761  -0.0691   0.7204   0.0036
  -7.500  -0.3972   0.01390   0.00719  -0.0677   0.7130   0.0038
  -7.250  -0.3784   0.01354   0.00680  -0.0665   0.7071   0.0040
  -7.000  -0.3585   0.01328   0.00651  -0.0654   0.7009   0.0042
  -6.750  -0.3395   0.01300   0.00617  -0.0642   0.6953   0.0045
  -6.500  -0.3199   0.01272   0.00586  -0.0630   0.6900   0.0049
  -6.250  -0.3005   0.01245   0.00556  -0.0618   0.6841   0.0053
  -6.000  -0.2822   0.01217   0.00524  -0.0604   0.6789   0.0058
  -5.750  -0.2634   0.01188   0.00493  -0.0590   0.6735   0.0074
  -5.500  -0.2446   0.01162   0.00466  -0.0576   0.6683   0.0092
  -5.250  -0.2266   0.01138   0.00440  -0.0561   0.6636   0.0124
  -5.000  -0.2093   0.01108   0.00413  -0.0545   0.6595   0.0200
  -4.750  -0.1928   0.01080   0.00388  -0.0526   0.6549   0.0295
  -4.500  -0.1781   0.01056   0.00366  -0.0504   0.6501   0.0403
  -4.250  -0.1663   0.01035   0.00349  -0.0476   0.6457   0.0550
  -4.000  -0.1531   0.01005   0.00331  -0.0450   0.6415   0.0844
  -3.750  -0.1437   0.00955   0.00307  -0.0419   0.6373   0.1493
  -3.500  -0.1321   0.00908   0.00283  -0.0392   0.6334   0.2167
  -3.250  -0.1199   0.00857   0.00259  -0.0367   0.6299   0.2940
  -3.000  -0.1123   0.00772   0.00222  -0.0334   0.6263   0.4224
  -2.750  -0.1080   0.00644   0.00166  -0.0297   0.6225   0.6096
  -2.500  -0.0865   0.00619   0.00174  -0.0286   0.6186   0.7091
  -2.000  -0.0300   0.00639   0.00189  -0.0289   0.6121   0.7375
  -1.750  -0.0014   0.00652   0.00198  -0.0292   0.6088   0.7468
  -1.500   0.0272   0.00675   0.00222  -0.0293   0.6052   0.7545
  -1.250   0.0556   0.00683   0.00224  -0.0295   0.6017   0.7575
  -0.750   0.1127   0.00684   0.00216  -0.0303   0.5956   0.7589
  -0.500   0.1414   0.00684   0.00213  -0.0307   0.5923   0.7596
  -0.250   0.1699   0.00685   0.00210  -0.0311   0.5889   0.7601
   0.000   0.1982   0.00687   0.00207  -0.0314   0.5855   0.7605
   0.250   0.2263   0.00689   0.00205  -0.0317   0.5822   0.7611
   0.500   0.2550   0.00688   0.00204  -0.0321   0.5792   0.7617
   0.750   0.2835   0.00689   0.00203  -0.0325   0.5755   0.7622
   1.000   0.3117   0.00691   0.00204  -0.0328   0.5713   0.7628
   1.250   0.3392   0.00696   0.00205  -0.0330   0.5667   0.7634
   1.500   0.3677   0.00697   0.00207  -0.0334   0.5623   0.7640
   1.750   0.3958   0.00700   0.00209  -0.0337   0.5576   0.7646
   2.000   0.4235   0.00705   0.00212  -0.0339   0.5529   0.7651
   2.250   0.4513   0.00709   0.00215  -0.0342   0.5484   0.7657
   2.500   0.4795   0.00712   0.00218  -0.0345   0.5434   0.7662
   2.750   0.5069   0.00717   0.00222  -0.0347   0.5376   0.7668
   3.000   0.5343   0.00722   0.00226  -0.0348   0.5322   0.7673
   3.250   0.5620   0.00726   0.00231  -0.0351   0.5260   0.7679
   3.500   0.5886   0.00734   0.00237  -0.0351   0.5191   0.7685
   3.750   0.6161   0.00739   0.00242  -0.0353   0.5118   0.7691
   4.000   0.6422   0.00748   0.00249  -0.0353   0.5031   0.7697
   4.250   0.6689   0.00755   0.00256  -0.0353   0.4930   0.7703
   4.500   0.6948   0.00766   0.00264  -0.0352   0.4823   0.7709
   4.750   0.7197   0.00779   0.00274  -0.0350   0.4687   0.7716
   5.000   0.7441   0.00794   0.00285  -0.0346   0.4527   0.7723
   5.250   0.7668   0.00816   0.00299  -0.0339   0.4306   0.7731
   5.500   0.7875   0.00844   0.00318  -0.0329   0.4042   0.7738
   5.750   0.8066   0.00879   0.00340  -0.0315   0.3749   0.7744
   6.000   0.8247   0.00916   0.00365  -0.0300   0.3461   0.7750
   6.250   0.8425   0.00952   0.00390  -0.0285   0.3188   0.7755
   6.500   0.8593   0.00990   0.00417  -0.0267   0.2928   0.7760
   6.750   0.8726   0.01027   0.00444  -0.0243   0.2678   0.7767
   7.000   0.8871   0.01058   0.00468  -0.0221   0.2479   0.7776
   7.250   0.9008   0.01094   0.00498  -0.0198   0.2284   0.7784
   7.750   0.9259   0.01182   0.00571  -0.0149   0.1887   0.7800
   8.000   0.9351   0.01238   0.00617  -0.0120   0.1651   0.7809
   8.250   0.9446   0.01294   0.00665  -0.0093   0.1446   0.7817
   8.500   0.9548   0.01349   0.00714  -0.0067   0.1275   0.7825
   8.750   0.9669   0.01400   0.00762  -0.0046   0.1161   0.7834
   9.000   0.9763   0.01463   0.00819  -0.0022   0.1014   0.7844
   9.250   0.9857   0.01530   0.00881   0.0002   0.0886   0.7854
   9.500   0.9891   0.01625   0.00966   0.0032   0.0694   0.7865
   9.750   1.0013   0.01688   0.01029   0.0049   0.0632   0.7874
  10.000   1.0055   0.01791   0.01123   0.0075   0.0478   0.7883
  10.250   1.0124   0.01888   0.01215   0.0097   0.0379   0.7891
  10.500   1.0269   0.01950   0.01282   0.0108   0.0374   0.7899
  10.750   1.0341   0.02053   0.01381   0.0127   0.0290   0.7907
  11.000   1.0425   0.02155   0.01480   0.0143   0.0232   0.7913
  11.250   1.0539   0.02242   0.01570   0.0155   0.0213   0.7919
  11.500   1.0646   0.02337   0.01667   0.0168   0.0188   0.7926
  11.750   1.0723   0.02450   0.01781   0.0182   0.0150   0.7936
  12.000   1.0831   0.02548   0.01883   0.0193   0.0136   0.7946
  12.250   1.0920   0.02662   0.01999   0.0204   0.0116   0.7955
  12.500   1.1015   0.02774   0.02116   0.0215   0.0102   0.7965
  12.750   1.1119   0.02884   0.02230   0.0223   0.0097   0.7974
  13.000   1.1212   0.03004   0.02355   0.0232   0.0085   0.7982
  13.250   1.1289   0.03139   0.02493   0.0242   0.0070   0.7991
  13.500   1.1378   0.03269   0.02628   0.0249   0.0061   0.8001
  13.750   1.1451   0.03415   0.02777   0.0257   0.0048   0.8012
  14.000   1.1527   0.03563   0.02929   0.0264   0.0042   0.8022
  14.250   1.1575   0.03738   0.03107   0.0271   0.0028   0.8033
  14.500   1.1657   0.03890   0.03266   0.0276   0.0027   0.8042
  14.750   1.1731   0.04053   0.03434   0.0280   0.0025   0.8050
  15.000   1.1782   0.04239   0.03625   0.0284   0.0019   0.8059
  15.250   1.1848   0.04417   0.03810   0.0287   0.0018   0.8066
  15.500   1.1872   0.04640   0.04039   0.0290   0.0011   0.8074
  15.750   1.1932   0.04835   0.04240   0.0291   0.0010   0.8080
  16.000   1.1975   0.05049   0.04461   0.0291   0.0009   0.8088
  16.250   1.2026   0.05259   0.04679   0.0291   0.0009   0.8098
  16.500   1.2067   0.05485   0.04912   0.0290   0.0008   0.8108
  16.750   1.2089   0.05739   0.05174   0.0287   0.0007   0.8118
  17.000   1.2117   0.05993   0.05437   0.0284   0.0006   0.8128
  17.250   1.2135   0.06262   0.05714   0.0280   0.0006   0.8137
  17.500   1.2154   0.06538   0.05998   0.0274   0.0006   0.8147
  17.750   1.2101   0.06912   0.06383   0.0266   0.0004   0.8156
  18.000   1.2138   0.07180   0.06659   0.0258   0.0004   0.8166
  18.250   1.2144   0.07494   0.06982   0.0249   0.0004   0.8175
  18.500   1.2147   0.07819   0.07316   0.0238   0.0005   0.8184
  18.750   1.2064   0.08276   0.07786   0.0223   0.0004   0.8193
  19.000   1.2027   0.08678   0.08199   0.0207   0.0004   0.8201
<< Back to EPPLER 542 AIRFOIL (e542-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 542 AIRFOIL (e542-il)