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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 200,000
Max Cl/Cd: 75.47 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e212-il-200000-n5.txt
Download as CSV file: xf-e212-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E212  (10.55%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5504   0.07506   0.07130  -0.0483   1.0000   0.0144
 -10.250  -0.5748   0.06689   0.06310  -0.0529   1.0000   0.0143
 -10.000  -0.5970   0.06009   0.05626  -0.0569   1.0000   0.0142
  -9.750  -0.6233   0.05428   0.05038  -0.0601   1.0000   0.0141
  -9.500  -0.6488   0.05061   0.04667  -0.0605   1.0000   0.0140
  -9.250  -0.6662   0.04613   0.04199  -0.0629   1.0000   0.0140
  -9.000  -0.6741   0.04229   0.03788  -0.0636   1.0000   0.0140
  -8.750  -0.6743   0.03866   0.03391  -0.0640   1.0000   0.0140
  -8.500  -0.6615   0.03485   0.02964  -0.0660   0.9988   0.0140
  -8.250  -0.6347   0.03136   0.02564  -0.0695   0.9960   0.0141
  -8.000  -0.6061   0.02872   0.02258  -0.0720   0.9935   0.0142
  -7.750  -0.5772   0.02663   0.02013  -0.0739   0.9908   0.0144
  -7.500  -0.5476   0.02457   0.01783  -0.0757   0.9883   0.0147
  -7.250  -0.5164   0.02300   0.01610  -0.0775   0.9862   0.0150
  -7.000  -0.4848   0.02170   0.01468  -0.0792   0.9840   0.0154
  -6.750  -0.4554   0.02060   0.01346  -0.0803   0.9805   0.0159
  -6.500  -0.4237   0.01962   0.01236  -0.0817   0.9776   0.0166
  -6.250  -0.3901   0.01880   0.01141  -0.0835   0.9751   0.0180
  -6.000  -0.3553   0.01795   0.01045  -0.0855   0.9731   0.0190
  -5.750  -0.3266   0.01713   0.00955  -0.0862   0.9684   0.0200
  -5.500  -0.2933   0.01646   0.00876  -0.0877   0.9650   0.0215
  -5.250  -0.2579   0.01587   0.00804  -0.0895   0.9623   0.0236
  -5.000  -0.2255   0.01524   0.00739  -0.0908   0.9586   0.0279
  -4.750  -0.1942   0.01457   0.00678  -0.0919   0.9540   0.0454
  -4.500  -0.1595   0.01390   0.00629  -0.0937   0.9508   0.0866
  -4.250  -0.1233   0.01337   0.00592  -0.0959   0.9484   0.1295
  -4.000  -0.0944   0.01295   0.00565  -0.0964   0.9424   0.1703
  -3.750  -0.0606   0.01252   0.00539  -0.0979   0.9383   0.2208
  -3.500  -0.0244   0.01216   0.00515  -0.0998   0.9354   0.2635
  -3.250   0.0060   0.01190   0.00494  -0.1004   0.9295   0.2965
  -3.000   0.0392   0.01163   0.00474  -0.1015   0.9244   0.3287
  -2.750   0.0755   0.01136   0.00451  -0.1032   0.9211   0.3598
  -2.500   0.1059   0.01116   0.00435  -0.1037   0.9142   0.3872
  -2.250   0.1403   0.01094   0.00418  -0.1049   0.9089   0.4159
  -2.000   0.1787   0.01071   0.00400  -0.1070   0.9051   0.4451
  -1.750   0.2083   0.01056   0.00390  -0.1072   0.8959   0.4709
  -1.500   0.2467   0.01034   0.00374  -0.1093   0.8908   0.4981
  -1.250   0.2776   0.01021   0.00365  -0.1097   0.8809   0.5227
  -1.000   0.3133   0.01005   0.00354  -0.1112   0.8730   0.5480
  -0.750   0.3475   0.00991   0.00344  -0.1123   0.8631   0.5721
  -0.500   0.3803   0.00980   0.00338  -0.1130   0.8519   0.5958
  -0.250   0.4135   0.00970   0.00332  -0.1139   0.8399   0.6190
   0.000   0.4460   0.00962   0.00327  -0.1146   0.8265   0.6422
   0.250   0.4772   0.00958   0.00325  -0.1150   0.8115   0.6645
   0.500   0.5071   0.00955   0.00324  -0.1151   0.7952   0.6867
   0.750   0.5360   0.00956   0.00326  -0.1150   0.7778   0.7087
   1.000   0.5637   0.00959   0.00330  -0.1147   0.7595   0.7298
   1.250   0.5907   0.00964   0.00334  -0.1142   0.7408   0.7512
   1.500   0.6164   0.00971   0.00340  -0.1134   0.7211   0.7722
   1.750   0.6412   0.00979   0.00348  -0.1124   0.7007   0.7935
   2.000   0.6656   0.00990   0.00356  -0.1114   0.6799   0.8151
   2.250   0.6883   0.01000   0.00365  -0.1100   0.6582   0.8371
   2.500   0.7106   0.01012   0.00374  -0.1085   0.6361   0.8610
   2.750   0.7314   0.01023   0.00383  -0.1067   0.6133   0.8873
   3.000   0.7516   0.01033   0.00390  -0.1048   0.5904   0.9203
   3.250   0.7781   0.01042   0.00394  -0.1043   0.5653   1.0000
   3.500   0.8040   0.01070   0.00411  -0.1040   0.5399   1.0000
   3.750   0.8293   0.01100   0.00432  -0.1035   0.5135   1.0000
   4.000   0.8543   0.01132   0.00454  -0.1030   0.4864   1.0000
   4.250   0.8787   0.01166   0.00478  -0.1024   0.4586   1.0000
   4.500   0.9028   0.01203   0.00506  -0.1017   0.4303   1.0000
   4.750   0.9265   0.01242   0.00535  -0.1010   0.4019   1.0000
   5.000   0.9500   0.01284   0.00567  -0.1003   0.3742   1.0000
   5.500   0.9958   0.01376   0.00641  -0.0986   0.3151   1.0000
   5.750   1.0180   0.01429   0.00682  -0.0978   0.2834   1.0000
   6.000   1.0398   0.01485   0.00726  -0.0968   0.2515   1.0000
   6.250   1.0604   0.01552   0.00776  -0.0958   0.2145   1.0000
   6.500   1.0804   0.01627   0.00832  -0.0947   0.1761   1.0000
   6.750   1.1006   0.01701   0.00890  -0.0936   0.1443   1.0000
   7.000   1.1212   0.01772   0.00950  -0.0926   0.1197   1.0000
   7.250   1.1411   0.01847   0.01016  -0.0915   0.0965   1.0000
   7.500   1.1601   0.01931   0.01088  -0.0903   0.0740   1.0000
   7.750   1.1789   0.02014   0.01163  -0.0890   0.0546   1.0000
   8.000   1.1963   0.02109   0.01249  -0.0875   0.0369   1.0000
   8.250   1.2127   0.02211   0.01346  -0.0859   0.0254   1.0000
   8.500   1.2291   0.02310   0.01446  -0.0842   0.0200   1.0000
   8.750   1.2452   0.02401   0.01548  -0.0824   0.0176   1.0000
   9.250   1.2722   0.02602   0.01768  -0.0782   0.0153   1.0000
   9.500   1.2846   0.02706   0.01884  -0.0760   0.0146   1.0000
   9.750   1.2959   0.02816   0.02004  -0.0738   0.0138   1.0000
  10.000   1.3057   0.02936   0.02135  -0.0715   0.0130   1.0000
  10.250   1.3115   0.03086   0.02296  -0.0689   0.0125   1.0000
  10.500   1.3196   0.03222   0.02445  -0.0666   0.0121   1.0000
  10.750   1.3261   0.03374   0.02611  -0.0643   0.0118   1.0000
  11.000   1.3312   0.03541   0.02793  -0.0621   0.0115   1.0000
  11.250   1.3355   0.03723   0.02989  -0.0600   0.0113   1.0000
  11.500   1.3389   0.03921   0.03201  -0.0581   0.0111   1.0000
  11.750   1.3417   0.04133   0.03428  -0.0564   0.0109   1.0000
  12.000   1.3439   0.04362   0.03671  -0.0549   0.0107   1.0000
  12.250   1.3453   0.04609   0.03933  -0.0536   0.0106   1.0000
  12.500   1.3460   0.04874   0.04215  -0.0526   0.0104   1.0000
  12.750   1.3459   0.05160   0.04515  -0.0518   0.0103   1.0000
  13.000   1.3450   0.05467   0.04839  -0.0513   0.0102   1.0000
  13.250   1.3432   0.05798   0.05186  -0.0511   0.0101   1.0000
  13.500   1.3405   0.06155   0.05559  -0.0511   0.0100   1.0000
  13.750   1.3365   0.06540   0.05961  -0.0515   0.0099   1.0000
  14.000   1.3314   0.06958   0.06397  -0.0523   0.0098   1.0000
  14.250   1.3252   0.07410   0.06866  -0.0534   0.0098   1.0000
  14.500   1.3178   0.07897   0.07372  -0.0549   0.0097   1.0000
  14.750   1.3093   0.08425   0.07919  -0.0569   0.0097   1.0000
  15.000   1.2997   0.08996   0.08509  -0.0593   0.0097   1.0000
  15.250   1.2888   0.09614   0.09147  -0.0623   0.0096   1.0000
  15.500   1.2768   0.10281   0.09834  -0.0658   0.0096   1.0000
  15.750   1.2637   0.11001   0.10574  -0.0699   0.0096   1.0000
  16.000   1.2496   0.11777   0.11371  -0.0745   0.0096   1.0000
  16.250   1.2337   0.12631   0.12247  -0.0799   0.0097   1.0000
  16.500   1.2158   0.13586   0.13224  -0.0862   0.0098   1.0000
  16.750   1.1934   0.14728   0.14389  -0.0938   0.0099   1.0000
  17.000   1.1588   0.16346   0.16036  -0.1047   0.0101   1.0000
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