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EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il)
Reynolds number: 100,000
Max Cl/Cd: 29.11 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ea61012-il-100000-n5.txt
Download as CSV file: xf-ea61012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 6(-1)-012 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7863   0.09461   0.08884  -0.0143   1.0000   0.0587
 -12.750  -0.8539   0.07852   0.07257  -0.0259   1.0000   0.0580
 -12.500  -0.8967   0.07006   0.06389  -0.0307   1.0000   0.0578
 -12.250  -0.9289   0.06421   0.05781  -0.0326   1.0000   0.0578
 -12.000  -0.9557   0.05967   0.05301  -0.0328   1.0000   0.0580
 -11.750  -0.9797   0.05602   0.04908  -0.0313   1.0000   0.0584
 -11.500  -0.9993   0.05302   0.04577  -0.0285   1.0000   0.0590
 -11.250  -1.0124   0.05004   0.04237  -0.0260   1.0000   0.0597
 -11.000  -1.0063   0.04764   0.03983  -0.0249   1.0000   0.0606
 -10.750  -0.9943   0.04577   0.03786  -0.0240   1.0000   0.0615
 -10.500  -0.9831   0.04383   0.03576  -0.0229   1.0000   0.0623
 -10.250  -0.9707   0.04188   0.03360  -0.0218   1.0000   0.0632
 -10.000  -0.9573   0.03998   0.03148  -0.0208   1.0000   0.0641
  -9.750  -0.9425   0.03816   0.02943  -0.0197   1.0000   0.0652
  -9.500  -0.9269   0.03651   0.02751  -0.0187   1.0000   0.0668
  -9.250  -0.9105   0.03494   0.02562  -0.0176   1.0000   0.0684
  -9.000  -0.8913   0.03340   0.02384  -0.0168   1.0000   0.0695
  -8.750  -0.8686   0.03191   0.02232  -0.0165   1.0000   0.0705
  -8.500  -0.8461   0.03064   0.02100  -0.0161   1.0000   0.0716
  -8.250  -0.8234   0.02946   0.01976  -0.0156   1.0000   0.0728
  -8.000  -0.8005   0.02835   0.01857  -0.0151   1.0000   0.0741
  -7.750  -0.7774   0.02730   0.01743  -0.0146   1.0000   0.0755
  -7.500  -0.7545   0.02638   0.01640  -0.0140   1.0000   0.0775
  -7.250  -0.7318   0.02553   0.01545  -0.0134   1.0000   0.0795
  -7.000  -0.7097   0.02456   0.01459  -0.0128   1.0000   0.0814
  -6.750  -0.6885   0.02376   0.01382  -0.0120   1.0000   0.0833
  -6.500  -0.6685   0.02302   0.01311  -0.0110   1.0000   0.0850
  -6.250  -0.6513   0.02237   0.01246  -0.0095   1.0000   0.0869
  -6.000  -0.6248   0.02168   0.01173  -0.0098   0.9880   0.0892
  -5.750  -0.5925   0.02089   0.01094  -0.0113   0.9723   0.0920
  -5.500  -0.5603   0.02016   0.01025  -0.0128   0.9592   0.0956
  -5.250  -0.5281   0.01958   0.00963  -0.0141   0.9476   0.1011
  -5.000  -0.4971   0.01893   0.00902  -0.0152   0.9371   0.1083
  -4.750  -0.4662   0.01838   0.00846  -0.0162   0.9281   0.1180
  -4.500  -0.4389   0.01777   0.00797  -0.0165   0.9188   0.1329
  -4.250  -0.4118   0.01709   0.00748  -0.0168   0.9112   0.1657
  -4.000  -0.3896   0.01631   0.00706  -0.0163   0.9022   0.2307
  -3.750  -0.3685   0.01542   0.00671  -0.0156   0.8947   0.3369
  -3.500  -0.3493   0.01476   0.00651  -0.0142   0.8864   0.4316
  -3.250  -0.3282   0.01448   0.00681  -0.0124   0.8800   0.5408
  -3.000  -0.3035   0.01453   0.00695  -0.0114   0.8739   0.5965
  -2.750  -0.2783   0.01466   0.00711  -0.0104   0.8678   0.6323
  -2.500  -0.2527   0.01492   0.00741  -0.0092   0.8626   0.6683
  -2.250  -0.2288   0.01529   0.00782  -0.0077   0.8562   0.6994
  -2.000  -0.2044   0.01563   0.00815  -0.0062   0.8506   0.7243
  -1.750  -0.1786   0.01595   0.00847  -0.0049   0.8465   0.7433
  -1.500  -0.1541   0.01611   0.00861  -0.0039   0.8406   0.7570
  -1.250  -0.1283   0.01616   0.00862  -0.0033   0.8352   0.7662
  -1.000  -0.1012   0.01617   0.00858  -0.0028   0.8305   0.7727
  -0.750  -0.0761   0.01619   0.00858  -0.0023   0.8233   0.7796
  -0.500  -0.0503   0.01617   0.00851  -0.0017   0.8167   0.7864
  -0.250  -0.0251   0.01618   0.00854  -0.0009   0.8086   0.7932
   0.000   0.0000   0.01617   0.00850   0.0000   0.8015   0.8015
   0.250   0.0251   0.01618   0.00854   0.0009   0.7932   0.8086
   0.500   0.0503   0.01617   0.00851   0.0017   0.7864   0.8167
   0.750   0.0761   0.01619   0.00858   0.0023   0.7796   0.8233
   1.000   0.1012   0.01617   0.00858   0.0028   0.7728   0.8305
   1.250   0.1283   0.01616   0.00862   0.0033   0.7662   0.8352
   1.500   0.1541   0.01611   0.00862   0.0039   0.7570   0.8406
   1.750   0.1786   0.01595   0.00847   0.0049   0.7433   0.8465
   2.000   0.2044   0.01563   0.00816   0.0062   0.7244   0.8506
   2.250   0.2288   0.01529   0.00782   0.0077   0.6995   0.8562
   2.500   0.2527   0.01492   0.00742   0.0092   0.6685   0.8626
   2.750   0.2783   0.01466   0.00711   0.0104   0.6323   0.8678
   3.000   0.3035   0.01453   0.00695   0.0114   0.5966   0.8739
   3.250   0.3282   0.01448   0.00682   0.0124   0.5410   0.8800
   3.500   0.3493   0.01476   0.00651   0.0142   0.4312   0.8864
   3.750   0.3686   0.01542   0.00671   0.0156   0.3377   0.8947
   4.000   0.3896   0.01630   0.00706   0.0163   0.2312   0.9022
   4.500   0.4390   0.01777   0.00796   0.0165   0.1329   0.9188
   4.750   0.4662   0.01838   0.00846   0.0162   0.1181   0.9281
   5.000   0.4972   0.01893   0.00902   0.0152   0.1084   0.9372
   5.250   0.5281   0.01958   0.00963   0.0141   0.1012   0.9476
   5.500   0.5603   0.02016   0.01025   0.0128   0.0956   0.9592
   5.750   0.5925   0.02088   0.01094   0.0113   0.0920   0.9724
   6.000   0.6248   0.02168   0.01173   0.0098   0.0892   0.9881
   6.250   0.6512   0.02237   0.01246   0.0095   0.0869   1.0000
   6.500   0.6685   0.02302   0.01310   0.0110   0.0851   1.0000
   6.750   0.6885   0.02376   0.01382   0.0120   0.0833   1.0000
   7.000   0.7098   0.02455   0.01458   0.0128   0.0814   1.0000
   7.250   0.7318   0.02553   0.01545   0.0134   0.0795   1.0000
   7.500   0.7546   0.02638   0.01640   0.0140   0.0774   1.0000
   7.750   0.7775   0.02730   0.01742   0.0146   0.0755   1.0000
   8.000   0.8006   0.02836   0.01858   0.0151   0.0741   1.0000
   8.250   0.8235   0.02946   0.01976   0.0156   0.0728   1.0000
   8.500   0.8462   0.03064   0.02100   0.0161   0.0716   1.0000
   8.750   0.8687   0.03191   0.02231   0.0165   0.0705   1.0000
   9.000   0.8914   0.03340   0.02383   0.0168   0.0695   1.0000
   9.250   0.9104   0.03494   0.02562   0.0176   0.0683   1.0000
   9.500   0.9269   0.03651   0.02752   0.0187   0.0667   1.0000
   9.750   0.9427   0.03817   0.02943   0.0197   0.0652   1.0000
  10.000   0.9574   0.03998   0.03149   0.0207   0.0641   1.0000
  10.250   0.9709   0.04189   0.03361   0.0218   0.0632   1.0000
  10.500   0.9832   0.04384   0.03577   0.0229   0.0624   1.0000
  10.750   0.9946   0.04576   0.03785   0.0239   0.0615   1.0000
  11.000   1.0067   0.04765   0.03983   0.0248   0.0605   1.0000
  11.250   1.0125   0.05005   0.04238   0.0260   0.0597   1.0000
  11.500   0.9991   0.05304   0.04580   0.0285   0.0589   1.0000
  11.750   0.9793   0.05607   0.04914   0.0313   0.0584   1.0000
  12.000   0.9561   0.05970   0.05305   0.0327   0.0580   1.0000
  12.250   0.9295   0.06424   0.05784   0.0325   0.0578   1.0000
  12.500   0.8964   0.07017   0.06401   0.0306   0.0578   1.0000
  12.750   0.8538   0.07864   0.07270   0.0257   0.0580   1.0000
  13.000   0.7839   0.09539   0.08963   0.0136   0.0587   1.0000
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