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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.01 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e392-il-1000000-n5.txt
Download as CSV file: xf-e392-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3456   0.09809   0.09646  -0.0350   1.0000   0.0051
  -9.500  -0.3431   0.09471   0.09309  -0.0360   0.9902   0.0049
  -8.500  -0.4508   0.02461   0.02146  -0.0961   0.8230   0.0035
  -8.250  -0.4353   0.02161   0.01802  -0.0964   0.8051   0.0036
  -8.000  -0.4150   0.01970   0.01578  -0.0964   0.7896   0.0036
  -7.750  -0.3926   0.01826   0.01407  -0.0964   0.7756   0.0037
  -7.500  -0.3689   0.01704   0.01260  -0.0963   0.7627   0.0038
  -7.250  -0.3444   0.01603   0.01136  -0.0963   0.7508   0.0039
  -6.750  -0.2935   0.01431   0.00923  -0.0962   0.7290   0.0042
  -6.500  -0.2674   0.01356   0.00830  -0.0961   0.7194   0.0044
  -6.000  -0.2142   0.01230   0.00674  -0.0961   0.7015   0.0048
  -5.750  -0.1873   0.01180   0.00611  -0.0960   0.6933   0.0050
  -5.500  -0.1600   0.01135   0.00553  -0.0960   0.6852   0.0051
  -5.250  -0.1327   0.01095   0.00502  -0.0960   0.6781   0.0052
  -5.000  -0.1052   0.01059   0.00457  -0.0960   0.6707   0.0053
  -4.750  -0.0778   0.01007   0.00395  -0.0961   0.6642   0.0055
  -4.500  -0.0501   0.00963   0.00342  -0.0961   0.6578   0.0060
  -4.000   0.0057   0.00913   0.00281  -0.0962   0.6455   0.0069
  -3.750   0.0338   0.00890   0.00251  -0.0963   0.6395   0.0073
  -3.500   0.0620   0.00871   0.00225  -0.0964   0.6343   0.0078
  -3.250   0.0902   0.00856   0.00204  -0.0964   0.6284   0.0082
  -3.000   0.1184   0.00838   0.00180  -0.0965   0.6230   0.0095
  -2.750   0.1468   0.00823   0.00163  -0.0966   0.6183   0.0111
  -2.500   0.1751   0.00804   0.00147  -0.0967   0.6129   0.0231
  -2.000   0.2316   0.00771   0.00126  -0.0970   0.6030   0.0675
  -1.750   0.2599   0.00759   0.00117  -0.0971   0.5979   0.0914
  -1.500   0.2880   0.00740   0.00111  -0.0973   0.5930   0.1391
  -1.250   0.3163   0.00718   0.00106  -0.0975   0.5883   0.1992
  -1.000   0.3446   0.00701   0.00102  -0.0977   0.5833   0.2512
  -0.750   0.3727   0.00687   0.00099  -0.0979   0.5785   0.3080
  -0.500   0.4010   0.00666   0.00098  -0.0981   0.5738   0.3853
  -0.250   0.4292   0.00654   0.00098  -0.0983   0.5687   0.4383
   0.000   0.4573   0.00647   0.00100  -0.0984   0.5639   0.4848
   0.250   0.4857   0.00639   0.00102  -0.0986   0.5591   0.5280
   0.500   0.5139   0.00633   0.00105  -0.0987   0.5538   0.5697
   0.750   0.5419   0.00630   0.00108  -0.0987   0.5489   0.6080
   1.000   0.5701   0.00624   0.00113  -0.0988   0.5437   0.6469
   1.250   0.5979   0.00620   0.00118  -0.0989   0.5380   0.6894
   1.500   0.6255   0.00615   0.00124  -0.0988   0.5323   0.7359
   1.750   0.6527   0.00610   0.00131  -0.0987   0.5248   0.7858
   2.000   0.6787   0.00604   0.00138  -0.0982   0.5169   0.8418
   2.250   0.7020   0.00597   0.00145  -0.0971   0.5082   0.9050
   2.500   0.7311   0.00591   0.00147  -0.0972   0.4998   1.0000
   2.750   0.7589   0.00602   0.00153  -0.0973   0.4908   1.0000
   3.000   0.7868   0.00613   0.00160  -0.0973   0.4806   1.0000
   3.250   0.8145   0.00624   0.00169  -0.0974   0.4700   1.0000
   3.500   0.8420   0.00638   0.00179  -0.0974   0.4584   1.0000
   3.750   0.8694   0.00653   0.00189  -0.0973   0.4452   1.0000
   4.000   0.8965   0.00669   0.00201  -0.0973   0.4309   1.0000
   4.250   0.9228   0.00695   0.00217  -0.0971   0.4070   1.0000
   4.500   0.9481   0.00730   0.00236  -0.0968   0.3707   1.0000
   4.750   0.9716   0.00785   0.00266  -0.0963   0.3180   1.0000
   5.000   0.9927   0.00865   0.00310  -0.0955   0.2483   1.0000
   5.250   1.0152   0.00929   0.00350  -0.0948   0.1993   1.0000
   5.500   1.0386   0.00982   0.00386  -0.0943   0.1637   1.0000
   5.750   1.0609   0.01045   0.00427  -0.0936   0.1239   1.0000
   6.000   1.0839   0.01097   0.00465  -0.0930   0.0959   1.0000
   6.250   1.1070   0.01148   0.00505  -0.0924   0.0730   1.0000
   6.500   1.1297   0.01200   0.00546  -0.0918   0.0528   1.0000
   6.750   1.1517   0.01257   0.00592  -0.0910   0.0340   1.0000
   7.000   1.1720   0.01328   0.00650  -0.0900   0.0135   1.0000
   7.250   1.1950   0.01371   0.00694  -0.0894   0.0105   1.0000
   7.500   1.2184   0.01408   0.00733  -0.0888   0.0095   1.0000
   7.750   1.2415   0.01447   0.00775  -0.0881   0.0090   1.0000
   8.000   1.2640   0.01488   0.00820  -0.0874   0.0085   1.0000
   8.250   1.2859   0.01533   0.00868  -0.0866   0.0082   1.0000
   8.500   1.3070   0.01581   0.00921  -0.0857   0.0078   1.0000
   8.750   1.3272   0.01634   0.00978  -0.0847   0.0075   1.0000
   9.000   1.3463   0.01692   0.01041  -0.0835   0.0072   1.0000
   9.250   1.3634   0.01760   0.01116  -0.0820   0.0068   1.0000
   9.500   1.3799   0.01828   0.01190  -0.0804   0.0066   1.0000
   9.750   1.3967   0.01882   0.01249  -0.0789   0.0065   1.0000
  10.000   1.4102   0.01942   0.01315  -0.0768   0.0063   1.0000
  10.250   1.4221   0.02009   0.01389  -0.0745   0.0062   1.0000
  10.500   1.4333   0.02082   0.01469  -0.0723   0.0061   1.0000
  10.750   1.4435   0.02166   0.01559  -0.0700   0.0059   1.0000
  11.000   1.4530   0.02258   0.01658  -0.0679   0.0058   1.0000
  11.250   1.4619   0.02359   0.01766  -0.0659   0.0057   1.0000
  11.500   1.4696   0.02475   0.01891  -0.0639   0.0055   1.0000
  11.750   1.4771   0.02600   0.02023  -0.0621   0.0054   1.0000
  12.000   1.4843   0.02735   0.02167  -0.0605   0.0053   1.0000
  12.250   1.4915   0.02878   0.02318  -0.0590   0.0052   1.0000
  12.500   1.4990   0.03025   0.02472  -0.0578   0.0050   1.0000
  12.750   1.5057   0.03187   0.02641  -0.0567   0.0049   1.0000
  13.000   1.5109   0.03371   0.02832  -0.0557   0.0048   1.0000
  13.250   1.5135   0.03586   0.03057  -0.0547   0.0047   1.0000
  13.500   1.5138   0.03835   0.03315  -0.0538   0.0045   1.0000
  13.750   1.5120   0.04115   0.03606  -0.0531   0.0044   1.0000
  14.000   1.5055   0.04461   0.03964  -0.0525   0.0043   1.0000
  14.250   1.5107   0.04683   0.04195  -0.0523   0.0043   1.0000
  14.500   1.5139   0.04933   0.04454  -0.0522   0.0042   1.0000
  14.750   1.5165   0.05199   0.04731  -0.0522   0.0042   1.0000
  15.000   1.5203   0.05458   0.04999  -0.0523   0.0041   1.0000
  15.250   1.5231   0.05734   0.05285  -0.0525   0.0040   1.0000
  15.500   1.5219   0.06074   0.05636  -0.0530   0.0039   1.0000
  15.750   1.5206   0.06427   0.06000  -0.0536   0.0038   1.0000
  16.000   1.5191   0.06794   0.06378  -0.0544   0.0037   1.0000
  16.250   1.5162   0.07191   0.06786  -0.0554   0.0037   1.0000
  16.500   1.5133   0.07601   0.07207  -0.0565   0.0036   1.0000
  16.750   1.5087   0.08050   0.07667  -0.0580   0.0035   1.0000
  17.000   1.5047   0.08503   0.08131  -0.0595   0.0035   1.0000
  17.250   1.4980   0.09010   0.08649  -0.0614   0.0034   1.0000
  17.500   1.4915   0.09531   0.09182  -0.0635   0.0034   1.0000
  17.750   1.4844   0.10073   0.09736  -0.0658   0.0033   1.0000
  18.000   1.4773   0.10629   0.10303  -0.0683   0.0033   1.0000
  18.250   1.4684   0.11228   0.10914  -0.0712   0.0032   1.0000
  18.500   1.4603   0.11826   0.11523  -0.0741   0.0032   1.0000
  18.750   1.4516   0.12449   0.12157  -0.0774   0.0031   1.0000
  19.000   1.4411   0.13120   0.12840  -0.0810   0.0031   1.0000
  19.250   1.4311   0.13789   0.13520  -0.0847   0.0031   1.0000
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