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EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 542 AIRFOIL (e542-il)
Reynolds number: 200,000
Max Cl/Cd: 54.92 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e542-il-200000-n5.txt
Download as CSV file: xf-e542-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4517   0.10385   0.10020  -0.0547   1.0000   0.0094
 -12.750  -0.4766   0.09063   0.08699  -0.0608   1.0000   0.0094
 -12.500  -0.4835   0.08489   0.08127  -0.0645   1.0000   0.0091
 -12.250  -0.5037   0.07731   0.07361  -0.0689   1.0000   0.0089
 -12.000  -0.5296   0.07073   0.06693  -0.0715   1.0000   0.0087
 -11.750  -0.5566   0.06526   0.06134  -0.0719   1.0000   0.0084
 -11.500  -0.5813   0.06086   0.05679  -0.0709   1.0000   0.0086
 -11.250  -0.6080   0.05676   0.05251  -0.0684   1.0000   0.0087
 -11.000  -0.6354   0.05293   0.04851  -0.0647   1.0000   0.0081
 -10.750  -0.6465   0.04972   0.04508  -0.0631   0.9961   0.0085
 -10.500  -0.6514   0.04562   0.04065  -0.0625   0.9784   0.0084
 -10.250  -0.6567   0.04099   0.03540  -0.0613   0.9602   0.0092
 -10.000  -0.6441   0.03761   0.03159  -0.0618   0.9483   0.0092
  -9.750  -0.6244   0.03428   0.02765  -0.0627   0.9382   0.0094
  -9.500  -0.5955   0.03150   0.02454  -0.0646   0.9293   0.0096
  -9.250  -0.5624   0.02946   0.02224  -0.0668   0.9201   0.0097
  -9.000  -0.5246   0.02753   0.02005  -0.0694   0.9118   0.0099
  -8.750  -0.4887   0.02602   0.01834  -0.0716   0.9017   0.0102
  -8.500  -0.4520   0.02465   0.01680  -0.0738   0.8916   0.0107
  -8.250  -0.4191   0.02349   0.01548  -0.0753   0.8801   0.0110
  -8.000  -0.3911   0.02251   0.01432  -0.0758   0.8680   0.0117
  -7.750  -0.3674   0.02164   0.01335  -0.0758   0.8563   0.0122
  -7.500  -0.3460   0.02092   0.01254  -0.0753   0.8453   0.0129
  -7.250  -0.3273   0.02027   0.01180  -0.0742   0.8343   0.0141
  -7.000  -0.3085   0.01967   0.01107  -0.0731   0.8245   0.0151
  -6.750  -0.2901   0.01917   0.01048  -0.0718   0.8146   0.0180
  -6.500  -0.2727   0.01865   0.00992  -0.0704   0.8056   0.0218
  -6.250  -0.2562   0.01809   0.00932  -0.0688   0.7971   0.0274
  -6.000  -0.2407   0.01753   0.00879  -0.0671   0.7893   0.0391
  -5.750  -0.2272   0.01692   0.00830  -0.0650   0.7816   0.0642
  -5.500  -0.2151   0.01631   0.00786  -0.0627   0.7745   0.1034
  -5.250  -0.2076   0.01559   0.00740  -0.0598   0.7668   0.1628
  -5.000  -0.2061   0.01476   0.00688  -0.0557   0.7601   0.2407
  -4.750  -0.2170   0.01393   0.00646  -0.0493   0.7523   0.3294
  -4.500  -0.1649   0.01567   0.00990  -0.0494   0.7484   0.6597
  -4.250  -0.1654   0.01548   0.00962  -0.0445   0.7426   0.6902
  -4.000  -0.1740   0.01495   0.00901  -0.0385   0.7356   0.7125
  -3.750  -0.1668   0.01487   0.00878  -0.0349   0.7301   0.7305
  -3.500  -0.1460   0.01543   0.00922  -0.0330   0.7249   0.7454
  -3.250  -0.0954   0.01720   0.01089  -0.0351   0.7200   0.7562
  -3.000  -0.0450   0.01860   0.01216  -0.0375   0.7159   0.7657
  -2.750  -0.0416   0.01834   0.01178  -0.0335   0.7116   0.7766
  -2.500  -0.0117   0.01841   0.01177  -0.0338   0.7065   0.7778
  -2.250   0.0175   0.01843   0.01170  -0.0341   0.7017   0.7791
  -2.000   0.0457   0.01842   0.01158  -0.0343   0.6976   0.7807
  -1.750   0.0715   0.01838   0.01144  -0.0341   0.6936   0.7827
  -1.250   0.0940   0.01775   0.01069  -0.0292   0.6845   0.7931
  -1.000   0.1218   0.01771   0.01056  -0.0293   0.6808   0.7940
  -0.750   0.1483   0.01768   0.01048  -0.0293   0.6768   0.7951
  -0.500   0.1735   0.01765   0.01042  -0.0290   0.6725   0.7965
  -0.250   0.1978   0.01757   0.01030  -0.0286   0.6686   0.7980
   0.000   0.2220   0.01749   0.01015  -0.0282   0.6650   0.7998
   0.250   0.2439   0.01736   0.00999  -0.0275   0.6614   0.8020
   0.500   0.2611   0.01715   0.00976  -0.0261   0.6571   0.8050
   0.750   0.2765   0.01682   0.00939  -0.0247   0.6530   0.8087
   1.000   0.3023   0.01675   0.00929  -0.0246   0.6495   0.8095
   1.250   0.3290   0.01672   0.00922  -0.0246   0.6463   0.8103
   1.500   0.3524   0.01671   0.00924  -0.0240   0.6419   0.8114
   1.750   0.3766   0.01666   0.00921  -0.0237   0.6376   0.8125
   2.000   0.4016   0.01660   0.00913  -0.0235   0.6339   0.8134
   2.250   0.4280   0.01655   0.00904  -0.0236   0.6306   0.8144
   2.500   0.4497   0.01650   0.00905  -0.0228   0.6257   0.8158
   2.750   0.4730   0.01645   0.00903  -0.0223   0.6209   0.8174
   3.000   0.4979   0.01637   0.00893  -0.0222   0.6166   0.8188
   3.250   0.5217   0.01630   0.00887  -0.0219   0.6117   0.8201
   3.500   0.5443   0.01621   0.00883  -0.0215   0.6060   0.8216
   3.750   0.5694   0.01612   0.00874  -0.0215   0.6011   0.8229
   4.000   0.5945   0.01605   0.00868  -0.0215   0.5960   0.8244
   4.500   0.6421   0.01603   0.00876  -0.0205   0.5841   0.8260
   4.750   0.6651   0.01603   0.00883  -0.0199   0.5777   0.8268
   5.000   0.6880   0.01602   0.00888  -0.0193   0.5707   0.8276
   5.250   0.7124   0.01601   0.00890  -0.0189   0.5642   0.8284
   5.500   0.7338   0.01601   0.00899  -0.0181   0.5560   0.8294
   5.750   0.7573   0.01600   0.00902  -0.0176   0.5483   0.8303
   6.000   0.7783   0.01601   0.00911  -0.0166   0.5388   0.8314
   6.250   0.7999   0.01602   0.00919  -0.0158   0.5293   0.8324
   6.500   0.8213   0.01603   0.00923  -0.0149   0.5189   0.8337
   6.750   0.8403   0.01608   0.00936  -0.0136   0.5066   0.8352
   7.000   0.8591   0.01613   0.00947  -0.0124   0.4929   0.8367
   7.250   0.8768   0.01620   0.00956  -0.0109   0.4766   0.8379
   7.500   0.8921   0.01631   0.00966  -0.0090   0.4572   0.8391
   7.750   0.9035   0.01645   0.00980  -0.0063   0.4355   0.8403
   8.000   0.9104   0.01671   0.00999  -0.0028   0.4113   0.8414
   8.250   0.9166   0.01712   0.01035   0.0006   0.3855   0.8426
   8.500   0.9209   0.01770   0.01084   0.0041   0.3590   0.8439
   8.750   0.9244   0.01839   0.01145   0.0075   0.3333   0.8454
   9.000   0.9281   0.01915   0.01214   0.0106   0.3088   0.8469
   9.250   0.9310   0.02002   0.01294   0.0136   0.2858   0.8488
   9.500   0.9346   0.02096   0.01383   0.0163   0.2629   0.8507
   9.750   0.9386   0.02198   0.01480   0.0186   0.2419   0.8522
  10.000   0.9417   0.02314   0.01589   0.0208   0.2209   0.8537
  10.250   0.9460   0.02432   0.01703   0.0227   0.2006   0.8551
  10.500   0.9485   0.02561   0.01826   0.0248   0.1809   0.8564
  10.750   0.9515   0.02693   0.01955   0.0267   0.1638   0.8576
  11.000   0.9550   0.02830   0.02089   0.0283   0.1469   0.8589
  11.250   0.9594   0.02968   0.02227   0.0298   0.1316   0.8603
  11.500   0.9639   0.03113   0.02370   0.0311   0.1177   0.8617
  11.750   0.9688   0.03261   0.02518   0.0322   0.1054   0.8632
  12.000   0.9732   0.03417   0.02674   0.0333   0.0941   0.8647
  12.250   0.9788   0.03572   0.02830   0.0342   0.0838   0.8664
  12.500   0.9844   0.03732   0.02994   0.0350   0.0749   0.8682
  12.750   0.9896   0.03902   0.03167   0.0356   0.0672   0.8698
  13.000   0.9936   0.04086   0.03353   0.0363   0.0599   0.8713
  13.250   0.9979   0.04265   0.03538   0.0369   0.0535   0.8726
  13.500   1.0022   0.04452   0.03732   0.0375   0.0481   0.8740
  13.750   1.0049   0.04662   0.03945   0.0379   0.0435   0.8755
  14.000   1.0095   0.04863   0.04156   0.0382   0.0392   0.8770
  14.250   1.0118   0.05093   0.04392   0.0383   0.0359   0.8787
  14.500   1.0156   0.05316   0.04623   0.0383   0.0324   0.8803
  14.750   1.0184   0.05558   0.04872   0.0382   0.0297   0.8820
  15.000   1.0215   0.05807   0.05129   0.0379   0.0271   0.8837
  15.250   1.0229   0.06081   0.05412   0.0374   0.0250   0.8854
  15.500   1.0255   0.06345   0.05687   0.0370   0.0228   0.8870
  15.750   1.0247   0.06653   0.06003   0.0364   0.0215   0.8886
  16.000   1.0265   0.06939   0.06305   0.0358   0.0197   0.8905
  16.250   1.0258   0.07265   0.06641   0.0349   0.0185   0.8923
  16.500   1.0240   0.07613   0.07001   0.0339   0.0173   0.8944
  16.750   1.0237   0.07953   0.07354   0.0328   0.0160   0.8967
  17.000   1.0204   0.08345   0.07757   0.0314   0.0149   0.8989
  17.500   1.0138   0.09152   0.08594   0.0283   0.0132   0.9035
  17.750   1.0096   0.09584   0.09038   0.0265   0.0123   0.9062
  18.000   1.0031   0.10061   0.09526   0.0244   0.0118   0.9090
  18.250   0.9982   0.10523   0.10005   0.0223   0.0114   0.9119
  18.500   0.9932   0.11001   0.10499   0.0199   0.0105   0.9150
  18.750   0.9869   0.11507   0.11019   0.0173   0.0099   0.9184
  19.000   0.9789   0.12052   0.11575   0.0144   0.0094   0.9225
  19.250   0.9726   0.12573   0.12114   0.0116   0.0092   0.9275
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