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EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 540 AIRFOIL (e540-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.04 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e540-il-1000000.txt
Download as CSV file: xf-e540-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4759   0.01966   0.01422  -0.1001   0.8517   0.0046
  -9.250  -0.4569   0.01890   0.01331  -0.0989   0.8427   0.0045
  -9.000  -0.4386   0.01811   0.01241  -0.0977   0.8341   0.0044
  -8.750  -0.4206   0.01758   0.01180  -0.0965   0.8263   0.0044
  -8.500  -0.4057   0.01672   0.01083  -0.0947   0.8187   0.0044
  -8.250  -0.3918   0.01599   0.01000  -0.0929   0.8119   0.0045
  -8.000  -0.3745   0.01556   0.00951  -0.0916   0.8053   0.0044
  -7.750  -0.3612   0.01491   0.00878  -0.0896   0.7994   0.0045
  -7.500  -0.3484   0.01424   0.00804  -0.0875   0.7937   0.0048
  -7.250  -0.3337   0.01374   0.00746  -0.0857   0.7883   0.0051
  -7.000  -0.3170   0.01334   0.00702  -0.0842   0.7835   0.0052
  -6.750  -0.3007   0.01293   0.00657  -0.0827   0.7784   0.0055
  -6.500  -0.2842   0.01256   0.00614  -0.0811   0.7738   0.0058
  -6.250  -0.2694   0.01212   0.00564  -0.0792   0.7695   0.0073
  -6.000  -0.2554   0.01168   0.00519  -0.0771   0.7652   0.0096
  -5.750  -0.2448   0.01120   0.00473  -0.0744   0.7611   0.0191
  -5.500  -0.2364   0.01084   0.00441  -0.0712   0.7571   0.0339
  -5.250  -0.2253   0.01050   0.00415  -0.0685   0.7533   0.0534
  -5.000  -0.2103   0.01015   0.00390  -0.0665   0.7496   0.0800
  -4.750  -0.1963   0.00973   0.00363  -0.0644   0.7461   0.1231
  -4.500  -0.1817   0.00927   0.00336  -0.0625   0.7429   0.1783
  -4.250  -0.1789   0.00814   0.00286  -0.0588   0.7396   0.3282
  -4.000  -0.1788   0.00641   0.00207  -0.0549   0.7362   0.5660
  -3.750  -0.1558   0.00620   0.00217  -0.0542   0.7333   0.6719
  -3.500  -0.1269   0.00634   0.00225  -0.0545   0.7306   0.6877
  -3.250  -0.0980   0.00646   0.00233  -0.0548   0.7281   0.6954
  -3.000  -0.0691   0.00660   0.00243  -0.0552   0.7257   0.7033
  -2.750  -0.0402   0.00676   0.00258  -0.0554   0.7231   0.7094
  -2.500  -0.0112   0.00703   0.00282  -0.0557   0.7206   0.7172
  -2.250   0.0179   0.00736   0.00318  -0.0557   0.7182   0.7242
  -2.000   0.0475   0.00769   0.00348  -0.0561   0.7157   0.7300
  -1.750   0.0763   0.00772   0.00346  -0.0565   0.7135   0.7317
  -1.500   0.1051   0.00770   0.00341  -0.0570   0.7111   0.7325
  -1.250   0.1336   0.00761   0.00330  -0.0575   0.7086   0.7335
  -1.000   0.1622   0.00756   0.00322  -0.0579   0.7062   0.7342
  -0.750   0.1911   0.00753   0.00316  -0.0584   0.7037   0.7349
  -0.500   0.2203   0.00756   0.00314  -0.0590   0.7009   0.7356
  -0.250   0.2485   0.00752   0.00312  -0.0593   0.6983   0.7363
   0.000   0.2768   0.00750   0.00309  -0.0597   0.6952   0.7369
   0.250   0.3053   0.00748   0.00305  -0.0601   0.6920   0.7376
   0.500   0.3340   0.00748   0.00303  -0.0605   0.6889   0.7382
   0.750   0.3626   0.00749   0.00302  -0.0610   0.6857   0.7389
   1.000   0.3906   0.00747   0.00301  -0.0613   0.6823   0.7397
   1.250   0.4187   0.00745   0.00300  -0.0616   0.6786   0.7405
   1.500   0.4470   0.00746   0.00298  -0.0620   0.6749   0.7413
   1.750   0.4753   0.00747   0.00298  -0.0624   0.6712   0.7420
   2.000   0.5031   0.00744   0.00297  -0.0626   0.6673   0.7428
   2.250   0.5309   0.00743   0.00297  -0.0629   0.6631   0.7435
   2.500   0.5591   0.00747   0.00297  -0.0633   0.6588   0.7442
   2.750   0.5865   0.00745   0.00298  -0.0635   0.6544   0.7449
   3.000   0.6140   0.00744   0.00299  -0.0637   0.6494   0.7455
   3.250   0.6415   0.00749   0.00301  -0.0639   0.6444   0.7461
   3.500   0.6687   0.00747   0.00304  -0.0640   0.6388   0.7467
   3.750   0.6954   0.00746   0.00304  -0.0641   0.6325   0.7475
   4.000   0.7221   0.00744   0.00305  -0.0641   0.6257   0.7484
   4.250   0.7481   0.00746   0.00307  -0.0640   0.6179   0.7491
   4.500   0.7743   0.00747   0.00312  -0.0639   0.6087   0.7497
   4.750   0.7993   0.00751   0.00317  -0.0636   0.5970   0.7504
   5.000   0.8235   0.00758   0.00324  -0.0631   0.5824   0.7511
   5.250   0.8462   0.00769   0.00332  -0.0623   0.5635   0.7519
   5.500   0.8661   0.00789   0.00344  -0.0609   0.5362   0.7527
   5.750   0.8819   0.00821   0.00362  -0.0588   0.4998   0.7535
   6.000   0.8935   0.00867   0.00390  -0.0559   0.4552   0.7544
   6.250   0.9020   0.00917   0.00421  -0.0524   0.4100   0.7554
   6.500   0.9080   0.00966   0.00451  -0.0484   0.3684   0.7565
   6.750   0.9143   0.01021   0.00488  -0.0446   0.3286   0.7576
   7.000   0.9239   0.01073   0.00526  -0.0415   0.2955   0.7587
   7.250   0.9331   0.01129   0.00567  -0.0385   0.2639   0.7596
   7.750   0.9506   0.01249   0.00660  -0.0325   0.2057   0.7611
   8.000   0.9607   0.01303   0.00707  -0.0299   0.1817   0.7622
   8.250   0.9702   0.01363   0.00758  -0.0272   0.1594   0.7633
   8.500   0.9797   0.01428   0.00815  -0.0247   0.1388   0.7643
   8.750   0.9892   0.01496   0.00876  -0.0223   0.1191   0.7653
   9.000   0.9977   0.01573   0.00944  -0.0198   0.0995   0.7663
   9.250   1.0065   0.01653   0.01015  -0.0175   0.0815   0.7674
   9.500   1.0155   0.01737   0.01091  -0.0153   0.0653   0.7684
   9.750   1.0267   0.01812   0.01163  -0.0135   0.0547   0.7695
  10.000   1.0372   0.01896   0.01242  -0.0117   0.0441   0.7707
  10.250   1.0478   0.01981   0.01325  -0.0100   0.0357   0.7719
  10.500   1.0581   0.02071   0.01412  -0.0083   0.0286   0.7730
  10.750   1.0714   0.02147   0.01490  -0.0071   0.0250   0.7739
  11.000   1.0831   0.02235   0.01577  -0.0057   0.0218   0.7748
  11.250   1.0944   0.02326   0.01670  -0.0043   0.0185   0.7757
  11.500   1.1079   0.02403   0.01752  -0.0032   0.0170   0.7770
  11.750   1.1190   0.02497   0.01847  -0.0020   0.0147   0.7782
  12.000   1.1287   0.02605   0.01959  -0.0006   0.0125   0.7794
  12.250   1.1423   0.02688   0.02047   0.0003   0.0113   0.7805
  12.500   1.1517   0.02802   0.02163   0.0016   0.0092   0.7817
  12.750   1.1607   0.02924   0.02291   0.0028   0.0074   0.7829
  13.000   1.1699   0.03045   0.02413   0.0039   0.0061   0.7841
  13.250   1.1753   0.03200   0.02575   0.0053   0.0048   0.7853
  13.500   1.1848   0.03328   0.02709   0.0062   0.0044   0.7865
  13.750   1.1938   0.03463   0.02849   0.0071   0.0041   0.7877
  14.000   1.2018   0.03609   0.03001   0.0080   0.0038   0.7888
  14.250   1.2084   0.03769   0.03167   0.0088   0.0035   0.7902
  14.500   1.2064   0.04011   0.03422   0.0102   0.0030   0.7918
  14.750   1.2133   0.04180   0.03601   0.0108   0.0027   0.7933
  15.000   1.2210   0.04344   0.03772   0.0113   0.0025   0.7947
  15.250   1.2243   0.04556   0.03994   0.0119   0.0024   0.7961
  15.500   1.2299   0.04752   0.04199   0.0123   0.0024   0.7975
  15.750   1.2329   0.04980   0.04437   0.0126   0.0024   0.7990
  16.000   1.2362   0.05213   0.04678   0.0128   0.0022   0.8004
  16.250   1.2373   0.05476   0.04951   0.0129   0.0022   0.8017
  16.500   1.2372   0.05762   0.05246   0.0129   0.0021   0.8030
  16.750   1.2352   0.06078   0.05573   0.0127   0.0020   0.8045
  17.000   1.2366   0.06363   0.05868   0.0123   0.0020   0.8062
  17.250   1.2251   0.06824   0.06344   0.0116   0.0019   0.8076
  17.500   1.2178   0.07247   0.06781   0.0107   0.0019   0.8091
  17.750   1.2123   0.07666   0.07212   0.0095   0.0019   0.8106
  18.000   1.2012   0.08183   0.07744   0.0079   0.0018   0.8120
  18.250   1.1908   0.08707   0.08283   0.0059   0.0018   0.8134
  18.500   1.1757   0.09329   0.08920   0.0034   0.0018   0.8146
  18.750   1.1620   0.09952   0.09557   0.0007   0.0018   0.8158
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