Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E224 (10.17%) (e224-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.87 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e224-il-1000000.txt
Download as CSV file: xf-e224-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6541   0.05834   0.05658  -0.0462   1.0000   0.0071
 -10.500  -0.6767   0.04866   0.04674  -0.0561   1.0000   0.0072
 -10.250  -0.6979   0.04343   0.04137  -0.0602   1.0000   0.0070
 -10.000  -0.7235   0.04048   0.03829  -0.0580   1.0000   0.0070
  -9.750  -0.7447   0.03665   0.03424  -0.0553   1.0000   0.0069
  -9.500  -0.7657   0.03210   0.02933  -0.0516   1.0000   0.0067
  -9.250  -0.7709   0.02906   0.02599  -0.0483   1.0000   0.0066
  -9.000  -0.7781   0.02514   0.02164  -0.0445   1.0000   0.0064
  -8.750  -0.7581   0.02199   0.01809  -0.0450   0.9985   0.0063
  -8.500  -0.7296   0.01982   0.01564  -0.0465   0.9966   0.0064
  -8.250  -0.6983   0.01856   0.01422  -0.0481   0.9950   0.0066
  -8.000  -0.6677   0.01730   0.01280  -0.0494   0.9933   0.0068
  -7.750  -0.6387   0.01596   0.01130  -0.0502   0.9907   0.0070
  -7.500  -0.6083   0.01469   0.00987  -0.0513   0.9884   0.0070
  -7.250  -0.5763   0.01369   0.00874  -0.0526   0.9864   0.0072
  -7.000  -0.5428   0.01292   0.00788  -0.0541   0.9849   0.0076
  -6.750  -0.5094   0.01186   0.00668  -0.0557   0.9836   0.0082
  -6.500  -0.4806   0.01110   0.00585  -0.0562   0.9797   0.0088
  -6.250  -0.4484   0.01059   0.00528  -0.0573   0.9766   0.0094
  -6.000  -0.4144   0.01016   0.00482  -0.0587   0.9744   0.0102
  -5.750  -0.3804   0.00976   0.00437  -0.0601   0.9720   0.0110
  -5.500  -0.3495   0.00920   0.00376  -0.0608   0.9682   0.0133
  -5.250  -0.3212   0.00884   0.00338  -0.0609   0.9618   0.0173
  -5.000  -0.2903   0.00838   0.00296  -0.0616   0.9571   0.0284
  -4.750  -0.2633   0.00799   0.00266  -0.0615   0.9489   0.0482
  -4.500  -0.2340   0.00764   0.00239  -0.0619   0.9421   0.0729
  -4.250  -0.2075   0.00733   0.00217  -0.0616   0.9320   0.1004
  -4.000  -0.1806   0.00700   0.00196  -0.0615   0.9223   0.1374
  -3.750  -0.1538   0.00671   0.00178  -0.0613   0.9122   0.1786
  -3.500  -0.1274   0.00644   0.00163  -0.0611   0.9010   0.2205
  -3.250  -0.1006   0.00624   0.00150  -0.0608   0.8898   0.2558
  -3.000  -0.0739   0.00602   0.00138  -0.0606   0.8785   0.2993
  -2.750  -0.0472   0.00584   0.00129  -0.0604   0.8667   0.3413
  -2.500  -0.0202   0.00570   0.00120  -0.0602   0.8545   0.3768
  -2.250   0.0067   0.00558   0.00112  -0.0599   0.8417   0.4089
  -2.000   0.0338   0.00547   0.00106  -0.0597   0.8286   0.4449
  -1.750   0.0608   0.00536   0.00101  -0.0595   0.8153   0.4802
  -1.500   0.0878   0.00527   0.00097  -0.0593   0.8017   0.5150
  -1.250   0.1149   0.00520   0.00094  -0.0591   0.7877   0.5486
  -1.000   0.1420   0.00514   0.00092  -0.0589   0.7734   0.5800
  -0.750   0.1690   0.00510   0.00090  -0.0586   0.7586   0.6113
  -0.500   0.1960   0.00506   0.00090  -0.0584   0.7432   0.6411
  -0.250   0.2230   0.00505   0.00090  -0.0581   0.7276   0.6698
   0.250   0.2768   0.00503   0.00093  -0.0575   0.6951   0.7256
   0.500   0.3036   0.00504   0.00096  -0.0572   0.6782   0.7522
   0.750   0.3302   0.00505   0.00100  -0.0568   0.6603   0.7782
   1.000   0.3566   0.00509   0.00104  -0.0564   0.6420   0.8032
   1.500   0.4089   0.00519   0.00114  -0.0555   0.6039   0.8492
   1.750   0.4347   0.00526   0.00121  -0.0549   0.5841   0.8710
   2.000   0.4598   0.00533   0.00128  -0.0542   0.5642   0.8922
   2.250   0.4845   0.00542   0.00135  -0.0534   0.5425   0.9134
   2.500   0.5083   0.00552   0.00142  -0.0523   0.5207   0.9348
   3.000   0.5645   0.00578   0.00157  -0.0523   0.4731   0.9751
   3.250   0.5999   0.00596   0.00166  -0.0540   0.4469   0.9888
   3.500   0.6347   0.00617   0.00176  -0.0557   0.4184   1.0000
   3.750   0.6589   0.00641   0.00189  -0.0550   0.3888   1.0000
   4.000   0.6837   0.00665   0.00202  -0.0545   0.3613   1.0000
   4.250   0.7089   0.00690   0.00217  -0.0541   0.3361   1.0000
   4.500   0.7341   0.00717   0.00234  -0.0536   0.3079   1.0000
   4.750   0.7589   0.00749   0.00253  -0.0532   0.2763   1.0000
   5.000   0.7835   0.00784   0.00273  -0.0527   0.2425   1.0000
   5.250   0.8079   0.00823   0.00297  -0.0522   0.2101   1.0000
   5.500   0.8323   0.00861   0.00323  -0.0517   0.1794   1.0000
   5.750   0.8568   0.00899   0.00349  -0.0512   0.1538   1.0000
   6.000   0.8813   0.00937   0.00376  -0.0507   0.1296   1.0000
   6.250   0.9054   0.00979   0.00407  -0.0502   0.1061   1.0000
   6.500   0.9294   0.01022   0.00440  -0.0496   0.0862   1.0000
   6.750   0.9537   0.01061   0.00473  -0.0491   0.0703   1.0000
   7.000   0.9775   0.01105   0.00509  -0.0485   0.0548   1.0000
   7.250   1.0005   0.01157   0.00551  -0.0479   0.0389   1.0000
   7.500   1.0233   0.01210   0.00597  -0.0471   0.0265   1.0000
   7.750   1.0463   0.01261   0.00648  -0.0464   0.0203   1.0000
   8.000   1.0693   0.01310   0.00696  -0.0456   0.0176   1.0000
   8.250   1.0916   0.01367   0.00758  -0.0447   0.0153   1.0000
   8.500   1.1152   0.01406   0.00801  -0.0442   0.0143   1.0000
   8.750   1.1380   0.01451   0.00849  -0.0434   0.0130   1.0000
   9.000   1.1578   0.01528   0.00931  -0.0422   0.0115   1.0000
   9.250   1.1786   0.01589   0.01000  -0.0412   0.0107   1.0000
   9.500   1.2005   0.01637   0.01054  -0.0404   0.0100   1.0000
   9.750   1.2218   0.01688   0.01109  -0.0395   0.0092   1.0000
  10.000   1.2413   0.01753   0.01178  -0.0383   0.0085   1.0000
  10.250   1.2519   0.01892   0.01329  -0.0359   0.0076   1.0000
  10.500   1.2729   0.01934   0.01376  -0.0350   0.0073   1.0000
  10.750   1.2911   0.01995   0.01444  -0.0337   0.0068   1.0000
  11.000   1.3094   0.02051   0.01504  -0.0324   0.0064   1.0000
  11.250   1.3258   0.02112   0.01572  -0.0309   0.0060   1.0000
  11.500   1.3380   0.02184   0.01649  -0.0287   0.0057   1.0000
  11.750   1.3409   0.02309   0.01783  -0.0253   0.0054   1.0000
  12.000   1.3358   0.02489   0.01980  -0.0211   0.0051   1.0000
  12.250   1.3471   0.02570   0.02068  -0.0192   0.0050   1.0000
  12.500   1.3541   0.02684   0.02192  -0.0171   0.0049   1.0000
  12.750   1.3596   0.02813   0.02331  -0.0150   0.0047   1.0000
  13.000   1.3621   0.02972   0.02502  -0.0129   0.0046   1.0000
  13.250   1.3631   0.03153   0.02695  -0.0111   0.0046   1.0000
  13.500   1.3662   0.03330   0.02882  -0.0097   0.0044   1.0000
  13.750   1.3639   0.03568   0.03133  -0.0084   0.0043   1.0000
  14.000   1.3642   0.03797   0.03374  -0.0076   0.0042   1.0000
  14.250   1.3631   0.04056   0.03645  -0.0072   0.0041   1.0000
  14.500   1.3626   0.04327   0.03927  -0.0072   0.0040   1.0000
  14.750   1.3565   0.04682   0.04294  -0.0075   0.0040   1.0000
  15.000   1.3483   0.05090   0.04716  -0.0084   0.0040   1.0000
  15.250   1.3424   0.05494   0.05132  -0.0097   0.0039   1.0000
  15.500   1.3381   0.05899   0.05547  -0.0113   0.0038   1.0000
  15.750   1.3316   0.06359   0.06018  -0.0134   0.0038   1.0000
  16.000   1.3108   0.07073   0.06750  -0.0167   0.0038   1.0000
  16.250   1.2985   0.07690   0.07380  -0.0200   0.0037   1.0000
  16.500   1.2782   0.08474   0.08181  -0.0241   0.0038   1.0000
  16.750   1.2644   0.09178   0.08897  -0.0281   0.0038   1.0000
  17.000   1.2441   0.10030   0.09764  -0.0328   0.0038   1.0000
  17.250   1.2261   0.10871   0.10617  -0.0377   0.0038   1.0000
  17.500   1.2083   0.11730   0.11489  -0.0427   0.0037   1.0000
  17.750   1.1796   0.12848   0.12626  -0.0491   0.0039   1.0000
  18.000   1.1577   0.13865   0.13657  -0.0552   0.0039   1.0000
  18.250   1.1401   0.14808   0.14611  -0.0608   0.0039   1.0000
  18.500   1.1094   0.16126   0.15945  -0.0687   0.0040   1.0000
  18.750   1.0650   0.17967   0.17807  -0.0795   0.0042   1.0000
<< Back to E224 (10.17%) (e224-il)

Polar data table (+)

Polar graphs


<< Back to E224 (10.17%) (e224-il)