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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.54 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e174-il-1000000-n5.txt
Download as CSV file: xf-e174-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3059   0.08224   0.08011  -0.0442   0.8304   0.0048
  -8.250  -0.3045   0.07920   0.07697  -0.0451   0.8042   0.0047
  -7.750  -0.3061   0.07252   0.07018  -0.0475   0.7658   0.0045
  -7.500  -0.3102   0.06901   0.06665  -0.0492   0.7510   0.0045
  -7.250  -0.3077   0.06452   0.06212  -0.0535   0.7380   0.0044
  -7.000  -0.3020   0.05904   0.05658  -0.0594   0.7267   0.0043
  -6.750  -0.2926   0.05242   0.04987  -0.0663   0.7176   0.0042
  -6.250  -0.2847   0.01896   0.01472  -0.0810   0.7055   0.0046
  -6.000  -0.2606   0.01670   0.01204  -0.0810   0.6970   0.0047
  -5.750  -0.2349   0.01530   0.01033  -0.0810   0.6896   0.0049
  -5.500  -0.2086   0.01430   0.00910  -0.0809   0.6820   0.0050
  -5.250  -0.1819   0.01343   0.00803  -0.0809   0.6750   0.0051
  -5.000  -0.1549   0.01271   0.00713  -0.0808   0.6678   0.0051
  -4.750  -0.1276   0.01215   0.00643  -0.0808   0.6616   0.0052
  -4.500  -0.1011   0.01109   0.00517  -0.0807   0.6550   0.0055
  -4.250  -0.0738   0.01054   0.00453  -0.0806   0.6491   0.0058
  -4.000  -0.0463   0.01009   0.00399  -0.0806   0.6430   0.0059
  -3.500   0.0092   0.00933   0.00306  -0.0805   0.6319   0.0063
  -3.250   0.0371   0.00903   0.00269  -0.0805   0.6260   0.0066
  -3.000   0.0650   0.00877   0.00237  -0.0805   0.6211   0.0071
  -2.750   0.0932   0.00856   0.00210  -0.0805   0.6159   0.0076
  -2.500   0.1213   0.00840   0.00188  -0.0805   0.6104   0.0079
  -2.250   0.1494   0.00821   0.00164  -0.0805   0.6056   0.0085
  -2.000   0.1776   0.00805   0.00143  -0.0806   0.6006   0.0096
  -1.750   0.2058   0.00794   0.00129  -0.0806   0.5954   0.0111
  -1.500   0.2340   0.00782   0.00115  -0.0806   0.5907   0.0156
  -1.250   0.2621   0.00760   0.00105  -0.0807   0.5858   0.0487
  -1.000   0.2901   0.00745   0.00098  -0.0808   0.5809   0.0846
  -0.750   0.3182   0.00729   0.00093  -0.0809   0.5762   0.1254
  -0.500   0.3462   0.00710   0.00090  -0.0810   0.5711   0.1882
  -0.250   0.3739   0.00686   0.00089  -0.0811   0.5661   0.2773
   0.000   0.4019   0.00670   0.00088  -0.0813   0.5615   0.3414
   0.250   0.4296   0.00646   0.00090  -0.0814   0.5563   0.4416
   0.500   0.4573   0.00631   0.00092  -0.0814   0.5512   0.5176
   0.750   0.4849   0.00613   0.00095  -0.0815   0.5462   0.6016
   1.000   0.5117   0.00588   0.00100  -0.0813   0.5406   0.7152
   1.250   0.5361   0.00561   0.00107  -0.0805   0.5352   0.8393
   1.500   0.5624   0.00538   0.00109  -0.0798   0.5289   0.9645
   1.750   0.5954   0.00545   0.00111  -0.0810   0.5211   1.0000
   2.000   0.6234   0.00552   0.00115  -0.0810   0.5125   1.0000
   2.250   0.6512   0.00561   0.00119  -0.0810   0.5036   1.0000
   2.500   0.6788   0.00572   0.00125  -0.0810   0.4937   1.0000
   2.750   0.7066   0.00581   0.00132  -0.0810   0.4840   1.0000
   3.000   0.7342   0.00592   0.00139  -0.0810   0.4741   1.0000
   3.250   0.7617   0.00604   0.00147  -0.0809   0.4629   1.0000
   3.500   0.7891   0.00618   0.00157  -0.0809   0.4500   1.0000
   3.750   0.8162   0.00635   0.00168  -0.0808   0.4316   1.0000
   4.000   0.8421   0.00667   0.00183  -0.0806   0.3954   1.0000
   4.250   0.8677   0.00701   0.00202  -0.0804   0.3584   1.0000
   4.500   0.8919   0.00755   0.00231  -0.0800   0.3048   1.0000
   4.750   0.9129   0.00850   0.00281  -0.0792   0.2146   1.0000
   5.000   0.9358   0.00918   0.00320  -0.0787   0.1594   1.0000
   5.250   0.9599   0.00969   0.00354  -0.0783   0.1237   1.0000
   5.500   0.9832   0.01028   0.00395  -0.0778   0.0859   1.0000
   5.750   1.0063   0.01088   0.00437  -0.0772   0.0529   1.0000
   6.000   1.0287   0.01156   0.00487  -0.0766   0.0216   1.0000
   6.250   1.0522   0.01206   0.00531  -0.0760   0.0097   1.0000
   6.500   1.0770   0.01240   0.00567  -0.0756   0.0084   1.0000
   6.750   1.1016   0.01276   0.00605  -0.0752   0.0076   1.0000
   7.000   1.1258   0.01313   0.00646  -0.0748   0.0071   1.0000
   7.250   1.1500   0.01350   0.00686  -0.0743   0.0069   1.0000
   7.500   1.1737   0.01390   0.00730  -0.0738   0.0067   1.0000
   7.750   1.1970   0.01432   0.00777  -0.0732   0.0063   1.0000
   8.000   1.2197   0.01477   0.00827  -0.0726   0.0060   1.0000
   8.250   1.2418   0.01528   0.00882  -0.0719   0.0058   1.0000
   8.500   1.2633   0.01581   0.00940  -0.0711   0.0056   1.0000
   8.750   1.2840   0.01638   0.01002  -0.0702   0.0054   1.0000
   9.000   1.3037   0.01701   0.01071  -0.0691   0.0052   1.0000
   9.250   1.3221   0.01772   0.01148  -0.0679   0.0050   1.0000
   9.500   1.3387   0.01852   0.01236  -0.0665   0.0049   1.0000
   9.750   1.3523   0.01950   0.01342  -0.0646   0.0047   1.0000
  10.000   1.3614   0.02066   0.01468  -0.0622   0.0046   1.0000
  10.250   1.3717   0.02146   0.01555  -0.0597   0.0045   1.0000
  10.500   1.3827   0.02220   0.01637  -0.0575   0.0045   1.0000
  10.750   1.3901   0.02321   0.01745  -0.0551   0.0045   1.0000
  11.000   1.3988   0.02421   0.01853  -0.0530   0.0044   1.0000
  11.250   1.4063   0.02537   0.01978  -0.0511   0.0043   1.0000
  11.500   1.4131   0.02668   0.02118  -0.0493   0.0042   1.0000
  11.750   1.4185   0.02820   0.02279  -0.0476   0.0042   1.0000
  12.000   1.4237   0.02984   0.02453  -0.0462   0.0041   1.0000
  12.250   1.4276   0.03169   0.02647  -0.0449   0.0041   1.0000
  12.500   1.4363   0.03317   0.02803  -0.0441   0.0039   1.0000
  12.750   1.4394   0.03528   0.03026  -0.0431   0.0039   1.0000
  13.000   1.4434   0.03737   0.03245  -0.0424   0.0038   1.0000
  13.250   1.4458   0.03971   0.03489  -0.0418   0.0037   1.0000
  13.500   1.4473   0.04222   0.03751  -0.0413   0.0036   1.0000
  13.750   1.4478   0.04493   0.04033  -0.0410   0.0036   1.0000
  14.000   1.4494   0.04759   0.04309  -0.0408   0.0035   1.0000
  14.250   1.4473   0.05075   0.04638  -0.0408   0.0035   1.0000
  14.500   1.4445   0.05414   0.04989  -0.0410   0.0035   1.0000
  14.750   1.4432   0.05742   0.05328  -0.0414   0.0034   1.0000
  15.000   1.4394   0.06117   0.05715  -0.0421   0.0034   1.0000
  15.250   1.4341   0.06532   0.06143  -0.0430   0.0033   1.0000
  15.500   1.4303   0.06939   0.06561  -0.0441   0.0033   1.0000
  15.750   1.4238   0.07401   0.07037  -0.0456   0.0033   1.0000
  16.000   1.4172   0.07885   0.07533  -0.0472   0.0033   1.0000
  16.250   1.4104   0.08394   0.08056  -0.0492   0.0032   1.0000
  16.500   1.4024   0.08935   0.08610  -0.0515   0.0032   1.0000
  16.750   1.3925   0.09533   0.09222  -0.0542   0.0032   1.0000
  17.000   1.3839   0.10127   0.09828  -0.0570   0.0032   1.0000
  17.250   1.3702   0.10838   0.10554  -0.0605   0.0032   1.0000
  17.500   1.3595   0.11511   0.11239  -0.0640   0.0032   1.0000
  17.750   1.3469   0.12247   0.11988  -0.0680   0.0032   1.0000
  18.000   1.3337   0.13017   0.12772  -0.0724   0.0031   1.0000
  18.250   1.3198   0.13826   0.13594  -0.0771   0.0031   1.0000
  18.500   1.3054   0.14670   0.14451  -0.0821   0.0031   1.0000
  18.750   1.2906   0.15553   0.15347  -0.0876   0.0031   1.0000
  19.000   1.2755   0.16474   0.16282  -0.0933   0.0032   1.0000
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