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EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 326 AIRFOIL (e326-il)
Reynolds number: 500,000
Max Cl/Cd: 75.36 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e326-il-500000-n5.txt
Download as CSV file: xf-e326-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 326 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4309   0.08243   0.08038  -0.0163   1.0000   0.0072
 -10.000  -0.4408   0.07640   0.07437  -0.0192   1.0000   0.0071
  -9.750  -0.4596   0.06821   0.06618  -0.0250   1.0000   0.0070
  -9.500  -0.4867   0.06089   0.05879  -0.0288   1.0000   0.0070
  -9.250  -0.5102   0.05575   0.05357  -0.0294   1.0000   0.0069
  -9.000  -0.5325   0.05152   0.04926  -0.0282   1.0000   0.0069
  -8.750  -0.5533   0.04791   0.04557  -0.0254   1.0000   0.0068
  -8.500  -0.5613   0.04296   0.04043  -0.0248   0.9213   0.0066
  -8.000  -0.6518   0.03845   0.03492  -0.0097   0.9360   0.0051
  -7.750  -0.6345   0.03322   0.02905  -0.0098   0.8542   0.0050
  -7.500  -0.6331   0.02919   0.02442  -0.0055   0.8110   0.0049
  -7.250  -0.6225   0.02662   0.02139  -0.0025   0.7788   0.0048
  -7.000  -0.6087   0.02374   0.01799   0.0001   0.7539   0.0048
  -6.750  -0.5898   0.02159   0.01540   0.0019   0.7312   0.0047
  -6.500  -0.5679   0.02000   0.01346   0.0031   0.7112   0.0047
  -6.250  -0.5444   0.01876   0.01193   0.0040   0.6923   0.0047
  -6.000  -0.5203   0.01771   0.01066   0.0048   0.6749   0.0047
  -5.750  -0.4961   0.01676   0.00951   0.0056   0.6581   0.0048
  -5.500  -0.4724   0.01605   0.00864   0.0064   0.6426   0.0048
  -5.250  -0.4491   0.01535   0.00779   0.0074   0.6285   0.0049
  -5.000  -0.4261   0.01480   0.00712   0.0083   0.6144   0.0050
  -4.750  -0.4033   0.01431   0.00652   0.0093   0.6006   0.0051
  -4.500  -0.3804   0.01385   0.00596   0.0103   0.5881   0.0053
  -4.250  -0.3582   0.01336   0.00539   0.0114   0.5766   0.0055
  -4.000  -0.3352   0.01301   0.00497   0.0124   0.5650   0.0058
  -3.500  -0.2880   0.01246   0.00427   0.0141   0.5423   0.0069
  -3.250  -0.2643   0.01220   0.00394   0.0150   0.5326   0.0080
  -2.750  -0.2164   0.01176   0.00341   0.0165   0.5120   0.0131
  -2.500  -0.1927   0.01153   0.00318   0.0174   0.5029   0.0218
  -2.250  -0.1701   0.01122   0.00298   0.0183   0.4941   0.0512
  -2.000  -0.1486   0.01084   0.00281   0.0194   0.4860   0.1070
  -1.750  -0.1298   0.01031   0.00260   0.0210   0.4773   0.2062
  -1.500  -0.1370   0.00841   0.00210   0.0272   0.4717   0.5676
  -1.250  -0.1322   0.00773   0.00233   0.0325   0.4650   0.7996
  -1.000  -0.1073   0.00790   0.00246   0.0335   0.4577   0.8255
  -0.750  -0.0815   0.00806   0.00255   0.0342   0.4496   0.8392
  -0.500  -0.0556   0.00825   0.00266   0.0349   0.4423   0.8506
  -0.250  -0.0281   0.00846   0.00285   0.0354   0.4347   0.8592
   0.000  -0.0033   0.00861   0.00291   0.0362   0.4283   0.8675
   0.250   0.0251   0.00868   0.00293   0.0362   0.4215   0.8699
   0.500   0.0528   0.00873   0.00289   0.0362   0.4144   0.8710
   0.750   0.0807   0.00875   0.00286   0.0362   0.4082   0.8722
   1.000   0.1083   0.00879   0.00284   0.0362   0.4020   0.8734
   1.250   0.1359   0.00883   0.00282   0.0362   0.3960   0.8745
   1.500   0.1635   0.00886   0.00280   0.0362   0.3898   0.8756
   1.750   0.1908   0.00892   0.00280   0.0362   0.3842   0.8770
   2.000   0.2183   0.00896   0.00280   0.0362   0.3790   0.8783
   2.250   0.2457   0.00900   0.00280   0.0361   0.3731   0.8795
   2.500   0.2728   0.00907   0.00281   0.0362   0.3678   0.8807
   2.750   0.3004   0.00910   0.00283   0.0361   0.3630   0.8818
   3.000   0.3277   0.00916   0.00286   0.0361   0.3574   0.8829
   3.250   0.3550   0.00924   0.00291   0.0361   0.3523   0.8839
   3.500   0.3827   0.00930   0.00297   0.0360   0.3476   0.8850
   3.750   0.4101   0.00937   0.00304   0.0360   0.3423   0.8859
   4.000   0.4371   0.00947   0.00311   0.0360   0.3373   0.8869
   4.250   0.4647   0.00954   0.00319   0.0359   0.3326   0.8879
   4.500   0.4918   0.00962   0.00327   0.0359   0.3273   0.8890
   4.750   0.5186   0.00974   0.00338   0.0359   0.3222   0.8902
   5.000   0.5459   0.00981   0.00348   0.0359   0.3173   0.8914
   5.250   0.5727   0.00992   0.00358   0.0359   0.3116   0.8927
   5.500   0.5993   0.01004   0.00370   0.0359   0.3064   0.8940
   5.750   0.6262   0.01014   0.00383   0.0359   0.3007   0.8956
   6.000   0.6524   0.01028   0.00395   0.0360   0.2946   0.8971
   6.250   0.6791   0.01039   0.00410   0.0360   0.2887   0.8984
   6.500   0.7054   0.01052   0.00424   0.0360   0.2821   0.8995
   6.750   0.7314   0.01066   0.00441   0.0361   0.2760   0.9007
   7.000   0.7575   0.01081   0.00459   0.0363   0.2689   0.9020
   7.250   0.7829   0.01098   0.00478   0.0364   0.2621   0.9034
   7.500   0.8085   0.01115   0.00498   0.0366   0.2542   0.9049
   7.750   0.8336   0.01135   0.00520   0.0368   0.2462   0.9065
   8.000   0.8581   0.01157   0.00543   0.0371   0.2366   0.9082
   8.250   0.8828   0.01178   0.00567   0.0374   0.2275   0.9101
   8.500   0.9068   0.01204   0.00593   0.0377   0.2180   0.9121
   8.750   0.9299   0.01234   0.00623   0.0382   0.2069   0.9141
   9.000   0.9524   0.01265   0.00655   0.0388   0.1946   0.9161
   9.250   0.9743   0.01299   0.00690   0.0394   0.1819   0.9183
   9.500   0.9952   0.01338   0.00730   0.0402   0.1687   0.9207
   9.750   1.0147   0.01385   0.00773   0.0412   0.1541   0.9235
  10.000   1.0332   0.01435   0.00821   0.0422   0.1399   0.9266
  10.500   1.0661   0.01548   0.00930   0.0449   0.1123   0.9334
  10.750   1.0798   0.01612   0.00993   0.0467   0.0987   0.9380
  11.250   1.1052   0.01732   0.01118   0.0504   0.0795   0.9494
  11.750   1.1323   0.01894   0.01285   0.0527   0.0633   0.9667
  12.000   1.1503   0.02002   0.01396   0.0523   0.0552   0.9756
  12.250   1.1699   0.02118   0.01518   0.0511   0.0485   0.9850
  12.500   1.1887   0.02258   0.01663   0.0495   0.0432   0.9990
  12.750   1.1894   0.02403   0.01811   0.0511   0.0393   1.0000
  13.000   1.1889   0.02577   0.01991   0.0522   0.0361   1.0000
  13.250   1.1900   0.02766   0.02186   0.0528   0.0332   1.0000
  13.500   1.1884   0.03001   0.02426   0.0531   0.0306   1.0000
  13.750   1.1880   0.03241   0.02675   0.0530   0.0286   1.0000
  14.000   1.1859   0.03510   0.02951   0.0528   0.0264   1.0000
  14.250   1.1819   0.03807   0.03254   0.0523   0.0248   1.0000
  14.500   1.1767   0.04124   0.03580   0.0518   0.0231   1.0000
  14.750   1.1720   0.04443   0.03907   0.0511   0.0218   1.0000
  15.000   1.1654   0.04788   0.04261   0.0503   0.0206   1.0000
  15.250   1.1576   0.05154   0.04632   0.0494   0.0194   1.0000
  15.500   1.1484   0.05542   0.05030   0.0483   0.0187   1.0000
  15.750   1.1423   0.05909   0.05406   0.0472   0.0180   1.0000
  16.000   1.1361   0.06287   0.05793   0.0459   0.0173   1.0000
  16.250   1.1283   0.06695   0.06209   0.0445   0.0163   1.0000
  16.500   1.1205   0.07116   0.06637   0.0429   0.0157   1.0000
  16.750   1.1117   0.07558   0.07087   0.0412   0.0151   1.0000
  17.000   1.1040   0.07993   0.07530   0.0395   0.0146   1.0000
  17.250   1.0988   0.08400   0.07946   0.0379   0.0139   1.0000
  17.500   1.0924   0.08833   0.08388   0.0361   0.0133   1.0000
  17.750   1.0855   0.09280   0.08843   0.0341   0.0127   1.0000
  18.000   1.0778   0.09747   0.09319   0.0321   0.0123   1.0000
  18.250   1.0696   0.10234   0.09813   0.0299   0.0118   1.0000
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