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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 200,000
Max Cl/Cd: 68.25 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e224-il-200000.txt
Download as CSV file: xf-e224-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E224  (10.17%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.6126   0.03989   0.03495  -0.0449   1.0000   0.0292
  -7.250  -0.6119   0.03503   0.02983  -0.0429   1.0000   0.0278
  -7.000  -0.6052   0.03137   0.02577  -0.0407   1.0000   0.0270
  -6.750  -0.5941   0.02828   0.02225  -0.0386   1.0000   0.0266
  -6.500  -0.5793   0.02598   0.01957  -0.0368   1.0000   0.0269
  -6.250  -0.5622   0.02429   0.01757  -0.0352   1.0000   0.0279
  -6.000  -0.5433   0.02337   0.01636  -0.0336   1.0000   0.0293
  -5.750  -0.5241   0.02139   0.01411  -0.0322   1.0000   0.0297
  -5.500  -0.5047   0.01913   0.01172  -0.0309   1.0000   0.0310
  -5.250  -0.4847   0.01792   0.01050  -0.0297   1.0000   0.0333
  -5.000  -0.4640   0.01706   0.00956  -0.0286   1.0000   0.0367
  -4.750  -0.4436   0.01607   0.00856  -0.0276   1.0000   0.0433
  -4.500  -0.4214   0.01521   0.00767  -0.0269   0.9998   0.0531
  -4.250  -0.3828   0.01406   0.00673  -0.0296   0.9955   0.0954
  -4.000  -0.3456   0.01314   0.00625  -0.0323   0.9906   0.1851
  -3.750  -0.3068   0.01263   0.00606  -0.0352   0.9854   0.2669
  -3.500  -0.2694   0.01225   0.00592  -0.0376   0.9799   0.3447
  -3.250  -0.2318   0.01191   0.00581  -0.0399   0.9737   0.4163
  -3.000  -0.1926   0.01164   0.00573  -0.0424   0.9685   0.4801
  -2.750  -0.1577   0.01139   0.00561  -0.0439   0.9610   0.5369
  -2.500  -0.1163   0.01115   0.00553  -0.0465   0.9565   0.5940
  -2.250  -0.0843   0.01094   0.00545  -0.0472   0.9479   0.6422
  -2.000  -0.0435   0.01073   0.00535  -0.0494   0.9433   0.6909
  -1.750  -0.0106   0.01056   0.00529  -0.0500   0.9353   0.7321
  -1.500   0.0285   0.01037   0.00517  -0.0518   0.9302   0.7715
  -1.250   0.0607   0.01022   0.00508  -0.0520   0.9224   0.8063
  -1.000   0.0947   0.01005   0.00495  -0.0525   0.9156   0.8391
  -0.750   0.1229   0.00993   0.00487  -0.0517   0.9061   0.8697
  -0.500   0.1563   0.00976   0.00470  -0.0519   0.8993   0.8977
  -0.250   0.1861   0.00966   0.00460  -0.0514   0.8881   0.9237
   0.000   0.2246   0.00956   0.00446  -0.0529   0.8782   0.9457
   0.250   0.2708   0.00942   0.00427  -0.0561   0.8693   0.9619
   0.500   0.3183   0.00930   0.00411  -0.0598   0.8572   0.9758
   0.750   0.3677   0.00918   0.00394  -0.0640   0.8437   0.9874
   1.000   0.4167   0.00905   0.00376  -0.0683   0.8289   0.9995
   1.250   0.4373   0.00901   0.00363  -0.0669   0.8120   1.0000
   1.500   0.4560   0.00902   0.00359  -0.0651   0.7933   1.0000
   1.750   0.4762   0.00905   0.00356  -0.0635   0.7750   1.0000
   2.000   0.4976   0.00911   0.00354  -0.0621   0.7570   1.0000
   2.250   0.5194   0.00919   0.00355  -0.0608   0.7381   1.0000
   2.500   0.5416   0.00929   0.00359  -0.0595   0.7179   1.0000
   2.750   0.5647   0.00942   0.00364  -0.0583   0.6981   1.0000
   3.000   0.5879   0.00955   0.00372  -0.0573   0.6764   1.0000
   3.250   0.6117   0.00971   0.00379  -0.0563   0.6548   1.0000
   3.500   0.6353   0.00987   0.00391  -0.0553   0.6313   1.0000
   3.750   0.6591   0.01007   0.00405  -0.0543   0.6073   1.0000
   4.000   0.6828   0.01028   0.00418  -0.0534   0.5822   1.0000
   4.250   0.7064   0.01051   0.00435  -0.0524   0.5554   1.0000
   4.500   0.7299   0.01076   0.00456  -0.0515   0.5277   1.0000
   4.750   0.7531   0.01105   0.00477  -0.0505   0.4987   1.0000
   5.000   0.7760   0.01137   0.00500  -0.0495   0.4680   1.0000
   5.250   0.7985   0.01172   0.00527  -0.0485   0.4352   1.0000
   5.500   0.8209   0.01210   0.00559  -0.0475   0.4016   1.0000
   5.750   0.8428   0.01254   0.00593  -0.0465   0.3677   1.0000
   6.000   0.8645   0.01301   0.00630  -0.0454   0.3314   1.0000
   6.250   0.8853   0.01357   0.00673  -0.0443   0.2937   1.0000
   6.500   0.9053   0.01421   0.00719  -0.0432   0.2508   1.0000
   6.750   0.9249   0.01493   0.00774  -0.0420   0.2080   1.0000
   7.000   0.9445   0.01569   0.00835  -0.0409   0.1701   1.0000
   7.250   0.9635   0.01654   0.00905  -0.0397   0.1362   1.0000
   7.500   0.9817   0.01749   0.00985  -0.0384   0.1057   1.0000
   7.750   0.9981   0.01863   0.01088  -0.0368   0.0796   1.0000
   8.000   1.0114   0.02009   0.01219  -0.0347   0.0610   1.0000
   8.250   1.0250   0.02151   0.01361  -0.0327   0.0502   1.0000
   8.500   1.0426   0.02258   0.01480  -0.0311   0.0448   1.0000
   8.750   1.0562   0.02411   0.01631  -0.0292   0.0402   1.0000
   9.000   1.0729   0.02547   0.01780  -0.0277   0.0367   1.0000
   9.250   1.0900   0.02683   0.01927  -0.0262   0.0338   1.0000
   9.500   1.1060   0.02833   0.02079  -0.0248   0.0314   1.0000
   9.750   1.1222   0.03092   0.02353  -0.0236   0.0290   1.0000
  10.000   1.1385   0.03249   0.02535  -0.0221   0.0274   1.0000
  10.250   1.1537   0.03454   0.02763  -0.0206   0.0260   1.0000
  10.500   1.1663   0.03675   0.03007  -0.0189   0.0249   1.0000
  10.750   1.1756   0.03867   0.03216  -0.0170   0.0237   1.0000
  11.000   1.1826   0.04109   0.03469  -0.0152   0.0227   1.0000
  11.250   1.1795   0.04581   0.03973  -0.0129   0.0219   1.0000
  11.500   1.1701   0.04840   0.04261  -0.0096   0.0215   1.0000
  11.750   1.1608   0.05091   0.04541  -0.0069   0.0213   1.0000
  12.000   1.1489   0.05409   0.04886  -0.0049   0.0212   1.0000
  12.250   1.1344   0.05779   0.05283  -0.0037   0.0211   1.0000
  12.500   1.1182   0.06200   0.05728  -0.0034   0.0211   1.0000
  12.750   1.0997   0.06675   0.06226  -0.0041   0.0211   1.0000
  13.000   1.0803   0.07227   0.06798  -0.0058   0.0213   1.0000
  13.250   1.0602   0.07855   0.07444  -0.0085   0.0215   1.0000
  13.500   1.0385   0.08545   0.08152  -0.0123   0.0215   1.0000
  13.750   0.8562   0.10303   0.09997  -0.0229   0.0263   1.0000
  14.000   0.8108   0.11516   0.11221  -0.0310   0.0280   1.0000
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