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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 50,000
Max Cl/Cd: 33.7 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e224-il-50000.txt
Download as CSV file: xf-e224-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4444   0.09616   0.08938  -0.0120   1.0000   0.3035
  -8.000  -0.4341   0.09197   0.08520  -0.0118   1.0000   0.3072
  -7.750  -0.5185   0.07491   0.06849  -0.0364   1.0000   0.1386
  -7.500  -0.5381   0.06765   0.06118  -0.0408   1.0000   0.1252
  -7.250  -0.5592   0.06049   0.05368  -0.0440   1.0000   0.1149
  -7.000  -0.5567   0.05583   0.04890  -0.0436   1.0000   0.1116
  -6.750  -0.5575   0.05057   0.04325  -0.0436   1.0000   0.1077
  -6.500  -0.5527   0.04594   0.03810  -0.0430   1.0000   0.1062
  -6.250  -0.5412   0.04264   0.03450  -0.0419   1.0000   0.1090
  -6.000  -0.5279   0.03921   0.03059  -0.0408   1.0000   0.1118
  -5.750  -0.5114   0.03580   0.02657  -0.0396   1.0000   0.1144
  -5.500  -0.4930   0.03301   0.02351  -0.0383   1.0000   0.1212
  -5.250  -0.4731   0.03063   0.02078  -0.0370   1.0000   0.1330
  -5.000  -0.4524   0.02852   0.01858  -0.0356   1.0000   0.1492
  -4.750  -0.4312   0.02652   0.01647  -0.0342   1.0000   0.1750
  -4.500  -0.4114   0.02479   0.01495  -0.0326   1.0000   0.2185
  -4.250  -0.3929   0.02327   0.01376  -0.0308   1.0000   0.2876
  -4.000  -0.3761   0.02211   0.01312  -0.0285   1.0000   0.3701
  -3.750  -0.3603   0.02131   0.01273  -0.0256   1.0000   0.4530
  -3.500  -0.3455   0.02078   0.01251  -0.0222   1.0000   0.5297
  -3.250  -0.3319   0.02043   0.01236  -0.0182   1.0000   0.5994
  -3.000  -0.3197   0.02018   0.01226  -0.0139   1.0000   0.6657
  -2.750  -0.3103   0.02000   0.01223  -0.0087   1.0000   0.7264
  -2.500  -0.3034   0.01983   0.01215  -0.0030   1.0000   0.7866
  -2.250  -0.2949   0.01963   0.01201   0.0026   1.0000   0.8533
  -2.000  -0.2068   0.01991   0.01186  -0.0058   1.0000   0.9565
  -1.750  -0.1058   0.01945   0.01077  -0.0223   1.0000   1.0000
  -1.500  -0.1293   0.01880   0.01010  -0.0171   1.0000   1.0000
  -1.250  -0.1279   0.01859   0.00965  -0.0150   1.0000   1.0000
  -1.000  -0.1141   0.01865   0.00947  -0.0143   1.0000   1.0000
  -0.750  -0.0972   0.01884   0.00943  -0.0140   1.0000   1.0000
  -0.500  -0.0792   0.01911   0.00950  -0.0138   1.0000   1.0000
  -0.250  -0.0609   0.01944   0.00963  -0.0135   1.0000   1.0000
   0.000  -0.0426   0.01983   0.00987  -0.0134   1.0000   1.0000
   0.250  -0.0243   0.02029   0.01019  -0.0132   1.0000   1.0000
   0.500  -0.0062   0.02079   0.01058  -0.0131   1.0000   1.0000
   0.750   0.0117   0.02136   0.01105  -0.0130   1.0000   1.0000
   1.000   0.0293   0.02198   0.01157  -0.0130   1.0000   1.0000
   1.250   0.0572   0.02287   0.01239  -0.0150   0.9954   1.0000
   1.500   0.1113   0.02420   0.01367  -0.0217   0.9773   1.0000
   1.750   0.1640   0.02539   0.01484  -0.0279   0.9588   1.0000
   2.000   0.2146   0.02644   0.01589  -0.0333   0.9400   1.0000
   2.250   0.2590   0.02727   0.01677  -0.0374   0.9198   1.0000
   2.500   0.3096   0.02806   0.01763  -0.0422   0.9005   1.0000
   2.750   0.3506   0.02870   0.01835  -0.0452   0.8798   1.0000
   3.000   0.3964   0.02922   0.01900  -0.0485   0.8591   1.0000
   3.250   0.4431   0.02958   0.01950  -0.0517   0.8386   1.0000
   3.500   0.4862   0.02982   0.01989  -0.0539   0.8167   1.0000
   3.750   0.5410   0.02962   0.01994  -0.0573   0.7963   1.0000
   4.000   0.5802   0.02957   0.02006  -0.0580   0.7733   1.0000
   4.250   0.6238   0.02918   0.01992  -0.0588   0.7510   1.0000
   4.500   0.6682   0.02850   0.01945  -0.0590   0.7277   1.0000
   4.750   0.7017   0.02816   0.01928  -0.0579   0.7015   1.0000
   5.000   0.7363   0.02765   0.01897  -0.0565   0.6742   1.0000
   5.250   0.7694   0.02711   0.01856  -0.0548   0.6446   1.0000
   5.500   0.8015   0.02659   0.01811  -0.0528   0.6128   1.0000
   5.750   0.8280   0.02642   0.01803  -0.0505   0.5774   1.0000
   6.000   0.8551   0.02623   0.01780  -0.0481   0.5395   1.0000
   6.250   0.8772   0.02641   0.01794  -0.0455   0.4981   1.0000
   6.500   0.8988   0.02671   0.01812  -0.0428   0.4541   1.0000
   6.750   0.9186   0.02726   0.01847  -0.0402   0.4080   1.0000
   7.000   0.9349   0.02814   0.01926  -0.0375   0.3605   1.0000
   7.250   0.9511   0.02926   0.02016  -0.0349   0.3138   1.0000
   7.500   0.9670   0.03069   0.02136  -0.0325   0.2700   1.0000
   7.750   0.9823   0.03244   0.02294  -0.0303   0.2305   1.0000
   8.000   0.9995   0.03433   0.02450  -0.0285   0.1957   1.0000
   8.250   1.0161   0.03657   0.02660  -0.0267   0.1673   1.0000
   8.500   1.0303   0.03908   0.02941  -0.0247   0.1467   1.0000
   8.750   1.0480   0.04215   0.03273  -0.0232   0.1327   1.0000
   9.000   1.0627   0.04533   0.03615  -0.0216   0.1222   1.0000
   9.250   1.0812   0.04859   0.03937  -0.0207   0.1126   1.0000
   9.500   1.0830   0.05260   0.04409  -0.0180   0.1102   1.0000
   9.750   1.0812   0.05687   0.04891  -0.0156   0.1084   1.0000
  10.000   1.0750   0.06114   0.05362  -0.0133   0.1069   1.0000
  10.250   1.0635   0.06549   0.05833  -0.0112   0.1061   1.0000
  10.500   1.0446   0.07005   0.06320  -0.0092   0.1065   1.0000
  10.750   1.0184   0.07462   0.06798  -0.0075   0.1078   1.0000
  11.000   0.9916   0.07987   0.07337  -0.0075   0.1095   1.0000
  11.250   0.9682   0.08580   0.07938  -0.0090   0.1111   1.0000
  11.500   0.9505   0.09223   0.08586  -0.0113   0.1123   1.0000
  11.750   0.8754   0.10952   0.10306  -0.0257   0.1250   1.0000
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