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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 500,000
Max Cl/Cd: 89.22 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e224-il-500000.txt
Download as CSV file: xf-e224-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5096   0.09225   0.08996  -0.0314   1.0000   0.0219
 -10.250  -0.5184   0.08577   0.08351  -0.0345   1.0000   0.0220
 -10.000  -0.5286   0.08000   0.07777  -0.0372   1.0000   0.0225
  -7.750  -0.6835   0.02512   0.02047  -0.0395   1.0000   0.0119
  -7.500  -0.6691   0.02335   0.01838  -0.0375   0.9999   0.0115
  -7.250  -0.6374   0.02130   0.01602  -0.0391   0.9976   0.0114
  -7.000  -0.6072   0.01858   0.01302  -0.0405   0.9954   0.0116
  -6.750  -0.5755   0.01695   0.01125  -0.0419   0.9931   0.0122
  -6.500  -0.5432   0.01590   0.01012  -0.0432   0.9900   0.0129
  -6.250  -0.5095   0.01490   0.00902  -0.0448   0.9871   0.0135
  -6.000  -0.4739   0.01411   0.00811  -0.0466   0.9848   0.0146
  -5.750  -0.4373   0.01354   0.00747  -0.0486   0.9828   0.0156
  -5.500  -0.4084   0.01237   0.00623  -0.0493   0.9776   0.0181
  -5.250  -0.3731   0.01180   0.00560  -0.0509   0.9743   0.0211
  -5.000  -0.3367   0.01102   0.00475  -0.0529   0.9719   0.0293
  -4.750  -0.2996   0.01021   0.00411  -0.0551   0.9702   0.0604
  -4.500  -0.2702   0.00967   0.00375  -0.0556   0.9640   0.1016
  -4.250  -0.2350   0.00914   0.00343  -0.0575   0.9607   0.1517
  -4.000  -0.1995   0.00865   0.00315  -0.0594   0.9576   0.2080
  -3.750  -0.1688   0.00827   0.00292  -0.0601   0.9517   0.2563
  -3.500  -0.1370   0.00790   0.00270  -0.0609   0.9456   0.3053
  -3.250  -0.1059   0.00755   0.00251  -0.0617   0.9394   0.3600
  -3.000  -0.0770   0.00727   0.00235  -0.0618   0.9310   0.4036
  -2.750  -0.0483   0.00703   0.00221  -0.0619   0.9223   0.4439
  -2.500  -0.0193   0.00682   0.00208  -0.0620   0.9137   0.4837
  -2.250   0.0073   0.00664   0.00198  -0.0616   0.9024   0.5232
  -2.000   0.0343   0.00649   0.00190  -0.0613   0.8914   0.5606
  -1.750   0.0612   0.00635   0.00183  -0.0609   0.8800   0.5972
  -1.500   0.0881   0.00624   0.00177  -0.0604   0.8683   0.6313
  -1.250   0.1147   0.00616   0.00172  -0.0600   0.8559   0.6643
  -0.750   0.1674   0.00603   0.00167  -0.0589   0.8291   0.7251
  -0.500   0.1935   0.00599   0.00166  -0.0583   0.8154   0.7536
  -0.250   0.2195   0.00596   0.00166  -0.0576   0.8012   0.7810
   0.000   0.2452   0.00594   0.00167  -0.0569   0.7866   0.8074
   0.250   0.2705   0.00594   0.00169  -0.0560   0.7716   0.8324
   0.500   0.2956   0.00596   0.00171  -0.0552   0.7561   0.8569
   0.750   0.3201   0.00599   0.00173  -0.0541   0.7404   0.8796
   1.000   0.3443   0.00602   0.00176  -0.0530   0.7240   0.9019
   1.250   0.3683   0.00606   0.00178  -0.0518   0.7070   0.9237
   1.500   0.3940   0.00611   0.00180  -0.0511   0.6893   0.9448
   1.750   0.4250   0.00618   0.00182  -0.0515   0.6705   0.9629
   2.000   0.4610   0.00628   0.00185  -0.0532   0.6500   0.9773
   2.250   0.4992   0.00639   0.00189  -0.0554   0.6279   0.9884
   2.500   0.5383   0.00651   0.00193  -0.0579   0.6047   0.9979
   2.750   0.5634   0.00666   0.00200  -0.0575   0.5825   1.0000
   3.000   0.5856   0.00682   0.00207  -0.0564   0.5597   1.0000
   3.250   0.6087   0.00700   0.00217  -0.0554   0.5363   1.0000
   3.500   0.6326   0.00720   0.00228  -0.0547   0.5119   1.0000
   3.750   0.6569   0.00741   0.00241  -0.0540   0.4865   1.0000
   4.000   0.6813   0.00764   0.00256  -0.0534   0.4598   1.0000
   4.250   0.7057   0.00791   0.00271  -0.0527   0.4301   1.0000
   4.500   0.7300   0.00820   0.00290  -0.0521   0.3996   1.0000
   4.750   0.7546   0.00849   0.00310  -0.0516   0.3721   1.0000
   5.000   0.7789   0.00881   0.00332  -0.0510   0.3419   1.0000
   5.250   0.8028   0.00919   0.00357  -0.0504   0.3089   1.0000
   5.500   0.8266   0.00959   0.00385  -0.0498   0.2739   1.0000
   5.750   0.8496   0.01009   0.00416  -0.0491   0.2343   1.0000
   6.000   0.8726   0.01059   0.00450  -0.0484   0.1976   1.0000
   6.250   0.8957   0.01109   0.00486  -0.0478   0.1675   1.0000
   6.500   0.9188   0.01159   0.00525  -0.0471   0.1400   1.0000
   6.750   0.9416   0.01212   0.00567  -0.0464   0.1142   1.0000
   7.000   0.9642   0.01267   0.00612  -0.0457   0.0907   1.0000
   7.250   0.9864   0.01325   0.00661  -0.0449   0.0705   1.0000
   7.500   1.0073   0.01396   0.00721  -0.0439   0.0499   1.0000
   7.750   1.0279   0.01472   0.00790  -0.0428   0.0349   1.0000
   8.000   1.0480   0.01551   0.00871  -0.0416   0.0281   1.0000
   8.250   1.0692   0.01614   0.00937  -0.0406   0.0245   1.0000
   8.500   1.0864   0.01717   0.01046  -0.0390   0.0215   1.0000
   8.750   1.1076   0.01773   0.01110  -0.0380   0.0198   1.0000
   9.000   1.1268   0.01846   0.01190  -0.0368   0.0182   1.0000
   9.250   1.1417   0.01955   0.01304  -0.0350   0.0164   1.0000
   9.500   1.1536   0.02090   0.01451  -0.0327   0.0153   1.0000
   9.750   1.1731   0.02147   0.01518  -0.0316   0.0141   1.0000
  10.000   1.1882   0.02239   0.01619  -0.0299   0.0132   1.0000
  10.250   1.2013   0.02334   0.01720  -0.0280   0.0123   1.0000
  10.500   1.2068   0.02474   0.01867  -0.0250   0.0116   1.0000
  10.750   1.2049   0.02708   0.02118  -0.0212   0.0110   1.0000
  11.000   1.2150   0.02819   0.02242  -0.0191   0.0107   1.0000
  11.250   1.2232   0.02950   0.02387  -0.0169   0.0103   1.0000
  11.500   1.2295   0.03102   0.02553  -0.0148   0.0100   1.0000
  11.750   1.2342   0.03273   0.02738  -0.0127   0.0096   1.0000
  12.000   1.2387   0.03440   0.02918  -0.0109   0.0093   1.0000
  12.250   1.2426   0.03604   0.03095  -0.0094   0.0089   1.0000
  12.500   1.2450   0.03795   0.03297  -0.0081   0.0086   1.0000
  12.750   1.2455   0.04014   0.03525  -0.0070   0.0083   1.0000
  13.000   1.2430   0.04287   0.03811  -0.0062   0.0081   1.0000
  13.250   1.2388   0.04597   0.04136  -0.0057   0.0080   1.0000
  13.500   1.2220   0.05101   0.04662  -0.0055   0.0078   1.0000
  13.750   1.2100   0.05559   0.05141  -0.0061   0.0077   1.0000
  14.000   1.1920   0.06125   0.05731  -0.0077   0.0076   1.0000
  14.250   1.1827   0.06588   0.06210  -0.0096   0.0076   1.0000
  14.500   1.1721   0.07104   0.06744  -0.0122   0.0075   1.0000
  14.750   1.1559   0.07752   0.07410  -0.0154   0.0076   1.0000
  15.000   1.1379   0.08483   0.08160  -0.0195   0.0076   1.0000
  15.250   1.1215   0.09233   0.08927  -0.0241   0.0075   1.0000
  15.500   1.1048   0.10034   0.09744  -0.0291   0.0075   1.0000
  15.750   1.0858   0.10927   0.10652  -0.0346   0.0076   1.0000
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