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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 500,000
Max Cl/Cd: 58.73 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e521-il-500000.txt
Download as CSV file: xf-e521-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 521 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
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.9152   0.13310   0.13026   0.0081   1.0000   0.0061
 -17.750  -0.9310   0.12467   0.12169   0.0031   1.0000   0.0061
 -17.500  -0.9443   0.11702   0.11390  -0.0014   1.0000   0.0060
 -17.250  -0.9617   0.10877   0.10551  -0.0061   1.0000   0.0060
 -17.000  -0.9759   0.10148   0.09808  -0.0103   1.0000   0.0060
 -16.750  -0.9789   0.09636   0.09287  -0.0134   1.0000   0.0059
 -16.500  -1.0013   0.08804   0.08437  -0.0179   1.0000   0.0060
 -16.250  -1.0090   0.08250   0.07870  -0.0210   1.0000   0.0059
 -16.000  -1.0152   0.07738   0.07346  -0.0238   1.0000   0.0059
 -15.750  -1.0364   0.07021   0.06611  -0.0273   1.0000   0.0061
 -15.500  -1.0478   0.06484   0.06059  -0.0297   1.0000   0.0062
 -15.250  -1.0556   0.06021   0.05583  -0.0317   1.0000   0.0062
 -15.000  -1.0649   0.05564   0.05114  -0.0334   1.0000   0.0064
 -14.750  -1.0684   0.05206   0.04741  -0.0343   1.0000   0.0062
 -14.500  -1.0735   0.04851   0.04374  -0.0352   1.0000   0.0063
 -14.250  -1.0757   0.04551   0.04067  -0.0357   1.0000   0.0066
 -14.000  -1.0775   0.04267   0.03771  -0.0358   1.0000   0.0068
 -13.750  -1.0803   0.03987   0.03478  -0.0355   1.0000   0.0067
 -13.500  -1.0753   0.03796   0.03281  -0.0353   1.0000   0.0072
 -13.250  -1.0719   0.03595   0.03070  -0.0348   1.0000   0.0076
 -13.000  -1.0704   0.03383   0.02847  -0.0339   1.0000   0.0078
 -12.750  -1.0659   0.03205   0.02658  -0.0330   1.0000   0.0080
 -12.500  -1.0585   0.03056   0.02498  -0.0321   1.0000   0.0083
 -12.250  -1.0612   0.02832   0.02263  -0.0304   1.0000   0.0088
 -12.000  -1.0603   0.02645   0.02070  -0.0287   1.0000   0.0094
 -11.750  -1.0487   0.02542   0.01961  -0.0278   1.0000   0.0104
 -11.500  -1.0397   0.02421   0.01833  -0.0264   1.0000   0.0111
 -11.250  -1.0257   0.02336   0.01740  -0.0254   1.0000   0.0119
 -11.000  -1.0237   0.02173   0.01572  -0.0233   1.0000   0.0136
 -10.750  -1.0097   0.02090   0.01487  -0.0222   1.0000   0.0152
 -10.500  -0.9920   0.02030   0.01421  -0.0215   1.0000   0.0166
 -10.250  -0.9734   0.01901   0.01290  -0.0219   0.9622   0.0198
 -10.000  -0.9442   0.01859   0.01239  -0.0230   0.9389   0.0226
  -9.750  -0.9373   0.01776   0.01144  -0.0201   0.9199   0.0257
  -9.500  -0.9237   0.01736   0.01098  -0.0180   0.9098   0.0288
  -9.250  -0.9080   0.01687   0.01040  -0.0163   0.9017   0.0320
  -9.000  -0.8934   0.01625   0.00977  -0.0145   0.8952   0.0373
  -8.750  -0.8749   0.01574   0.00921  -0.0132   0.8895   0.0429
  -8.500  -0.8563   0.01524   0.00871  -0.0120   0.8846   0.0508
  -8.250  -0.8377   0.01470   0.00819  -0.0108   0.8802   0.0616
  -8.000  -0.8174   0.01420   0.00773  -0.0099   0.8757   0.0744
  -7.750  -0.7965   0.01374   0.00729  -0.0090   0.8718   0.0888
  -7.500  -0.7755   0.01331   0.00690  -0.0081   0.8684   0.1046
  -7.250  -0.7537   0.01287   0.00653  -0.0074   0.8648   0.1228
  -7.000  -0.7310   0.01247   0.00619  -0.0069   0.8611   0.1426
  -6.750  -0.7085   0.01206   0.00586  -0.0062   0.8579   0.1637
  -6.250  -0.6625   0.01134   0.00527  -0.0051   0.8519   0.2142
  -5.750  -0.6153   0.01057   0.00474  -0.0042   0.8455   0.2742
  -5.500  -0.5918   0.01020   0.00449  -0.0037   0.8425   0.3076
  -5.250  -0.5680   0.00986   0.00426  -0.0032   0.8397   0.3428
  -5.000  -0.5437   0.00954   0.00406  -0.0028   0.8370   0.3784
  -4.750  -0.5190   0.00921   0.00386  -0.0025   0.8337   0.4157
  -4.500  -0.4944   0.00889   0.00368  -0.0021   0.8306   0.4532
  -4.000  -0.4447   0.00837   0.00338  -0.0013   0.8249   0.5291
  -3.750  -0.4191   0.00815   0.00330  -0.0010   0.8217   0.5676
  -3.500  -0.3928   0.00799   0.00325  -0.0007   0.8181   0.6017
  -3.250  -0.3660   0.00790   0.00322  -0.0005   0.8147   0.6295
  -3.000  -0.3387   0.00787   0.00321  -0.0003   0.8116   0.6518
  -2.750  -0.3111   0.00789   0.00324  -0.0001   0.8085   0.6690
  -2.500  -0.2829   0.00790   0.00326  -0.0002   0.8045   0.6834
  -2.250  -0.2548   0.00793   0.00327  -0.0002   0.8006   0.6960
  -2.000  -0.2267   0.00797   0.00327  -0.0001   0.7971   0.7071
  -1.750  -0.1985   0.00803   0.00333   0.0000   0.7935   0.7155
  -1.500  -0.1701   0.00806   0.00334  -0.0001   0.7888   0.7242
  -1.250  -0.1418   0.00810   0.00337  -0.0001   0.7847   0.7313
  -1.000  -0.1135   0.00814   0.00336   0.0000   0.7810   0.7384
  -0.750  -0.0851   0.00817   0.00343   0.0000   0.7761   0.7443
  -0.500  -0.0567   0.00820   0.00341  -0.0001   0.7713   0.7513
  -0.250  -0.0284   0.00820   0.00342   0.0000   0.7672   0.7561
   0.000   0.0000   0.00822   0.00346   0.0000   0.7618   0.7618
   0.250   0.0284   0.00820   0.00342   0.0000   0.7561   0.7672
   0.500   0.0567   0.00820   0.00341   0.0001   0.7513   0.7713
   0.750   0.0851   0.00817   0.00343   0.0000   0.7443   0.7762
   1.000   0.1136   0.00814   0.00336   0.0000   0.7384   0.7810
   1.250   0.1418   0.00810   0.00337   0.0001   0.7312   0.7847
   1.500   0.1701   0.00806   0.00334   0.0001   0.7242   0.7889
   1.750   0.1985   0.00803   0.00333   0.0000   0.7156   0.7935
   2.000   0.2267   0.00797   0.00327   0.0001   0.7070   0.7971
   2.250   0.2548   0.00793   0.00327   0.0002   0.6960   0.8006
   2.500   0.2829   0.00790   0.00326   0.0002   0.6835   0.8045
   2.750   0.3111   0.00789   0.00324   0.0001   0.6690   0.8085
   3.000   0.3387   0.00787   0.00321   0.0003   0.6519   0.8116
   3.250   0.3660   0.00790   0.00322   0.0005   0.6295   0.8147
   3.500   0.3928   0.00799   0.00325   0.0007   0.6018   0.8181
   3.750   0.4191   0.00815   0.00330   0.0009   0.5676   0.8217
   4.000   0.4447   0.00837   0.00338   0.0013   0.5287   0.8249
   4.500   0.4944   0.00889   0.00368   0.0021   0.4534   0.8306
   4.750   0.5190   0.00921   0.00386   0.0025   0.4156   0.8338
   5.000   0.5437   0.00954   0.00406   0.0028   0.3782   0.8370
   5.250   0.5679   0.00986   0.00426   0.0032   0.3428   0.8397
   5.500   0.5917   0.01019   0.00449   0.0037   0.3077   0.8425
   5.750   0.6152   0.01056   0.00474   0.0042   0.2743   0.8455
   6.250   0.6624   0.01133   0.00527   0.0051   0.2141   0.8519
   6.500   0.6853   0.01171   0.00555   0.0057   0.1869   0.8549
   6.750   0.7083   0.01206   0.00586   0.0063   0.1638   0.8579
   7.000   0.7308   0.01247   0.00619   0.0069   0.1427   0.8612
   7.250   0.7535   0.01286   0.00653   0.0075   0.1228   0.8649
   7.500   0.7753   0.01331   0.00690   0.0082   0.1044   0.8684
   7.750   0.7963   0.01374   0.00729   0.0090   0.0888   0.8718
   8.000   0.8171   0.01419   0.00773   0.0099   0.0745   0.8758
   8.250   0.8374   0.01469   0.00819   0.0108   0.0617   0.8803
   8.500   0.8560   0.01524   0.00870   0.0121   0.0507   0.8847
   8.750   0.8744   0.01574   0.00921   0.0133   0.0429   0.8896
   9.000   0.8930   0.01625   0.00977   0.0145   0.0372   0.8953
   9.250   0.9075   0.01688   0.01041   0.0164   0.0319   0.9018
   9.500   0.9233   0.01735   0.01097   0.0181   0.0288   0.9099
   9.750   0.9369   0.01774   0.01142   0.0202   0.0257   0.9201
  10.000   0.9438   0.01858   0.01238   0.0231   0.0227   0.9394
  10.250   0.9728   0.01909   0.01299   0.0219   0.0200   0.9635
  10.500   0.9933   0.02021   0.01412   0.0214   0.0169   1.0000
  10.750   1.0092   0.02092   0.01489   0.0223   0.0152   1.0000
  11.000   1.0236   0.02171   0.01570   0.0233   0.0136   1.0000
  11.250   1.0264   0.02329   0.01732   0.0254   0.0119   1.0000
  11.500   1.0370   0.02437   0.01850   0.0267   0.0114   1.0000
  11.750   1.0490   0.02538   0.01957   0.0278   0.0103   1.0000
  12.000   1.0591   0.02652   0.02077   0.0289   0.0095   1.0000
  12.250   1.0632   0.02814   0.02245   0.0303   0.0089   1.0000
  12.500   1.0595   0.03044   0.02485   0.0320   0.0085   1.0000
  12.750   1.0680   0.03186   0.02639   0.0329   0.0079   1.0000
  13.000   1.0706   0.03380   0.02843   0.0339   0.0078   1.0000
  13.250   1.0750   0.03565   0.03038   0.0346   0.0073   1.0000
  13.500   1.0770   0.03779   0.03262   0.0352   0.0071   1.0000
  13.750   1.0774   0.04017   0.03511   0.0356   0.0069   1.0000
  14.000   1.0759   0.04284   0.03790   0.0358   0.0069   1.0000
  14.250   1.0768   0.04539   0.04054   0.0356   0.0066   1.0000
  14.500   1.0735   0.04852   0.04377   0.0352   0.0064   1.0000
  14.750   1.0697   0.05192   0.04728   0.0344   0.0063   1.0000
  15.000   1.0640   0.05578   0.05126   0.0332   0.0062   1.0000
  15.250   1.0541   0.06043   0.05605   0.0316   0.0061   1.0000
  15.500   1.0505   0.06447   0.06022   0.0298   0.0062   1.0000
  15.750   1.0388   0.06989   0.06577   0.0273   0.0061   1.0000
  16.000   1.0252   0.07585   0.07189   0.0244   0.0060   1.0000
  16.250   1.0184   0.08106   0.07723   0.0216   0.0061   1.0000
  16.500   1.0071   0.08712   0.08343   0.0183   0.0061   1.0000
  16.750   0.9857   0.09520   0.09168   0.0139   0.0059   1.0000
  17.000   0.9784   0.10108   0.09768   0.0105   0.0060   1.0000
  17.250   0.9642   0.10841   0.10515   0.0062   0.0060   1.0000
  17.500   0.9493   0.11610   0.11297   0.0018   0.0061   1.0000
  17.750   0.9325   0.12450   0.12151  -0.0031   0.0061   1.0000
  18.000   0.9141   0.13363   0.13082  -0.0085   0.0062   1.0000
  18.250   0.8888   0.14486   0.14224  -0.0150   0.0063   1.0000
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