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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 500,000
Max Cl/Cd: 136.84 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e216-il-500000.txt
Download as CSV file: xf-e216-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E216  (10.4%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2213   0.08376   0.08152  -0.0715   0.9724   0.0242
  -7.500  -0.2170   0.07696   0.07473  -0.0796   0.9666   0.0261
  -7.250  -0.2138   0.07185   0.06965  -0.0844   0.9601   0.0262
  -6.500  -0.1306   0.02377   0.01944  -0.1510   0.9427   0.0166
  -6.250  -0.0911   0.02202   0.01737  -0.1544   0.9418   0.0163
  -6.000  -0.0507   0.01956   0.01456  -0.1583   0.9413   0.0163
  -5.750  -0.0109   0.01735   0.01206  -0.1617   0.9409   0.0165
  -5.500   0.0284   0.01576   0.01033  -0.1647   0.9404   0.0169
  -5.250   0.0572   0.01503   0.00957  -0.1653   0.9365   0.0179
  -5.000   0.0902   0.01435   0.00884  -0.1666   0.9334   0.0188
  -4.750   0.1278   0.01356   0.00796  -0.1688   0.9319   0.0195
  -4.500   0.1664   0.01285   0.00717  -0.1712   0.9307   0.0205
  -4.250   0.2068   0.01204   0.00630  -0.1740   0.9297   0.0225
  -4.000   0.2458   0.01150   0.00572  -0.1764   0.9288   0.0257
  -3.750   0.2873   0.01067   0.00502  -0.1794   0.9281   0.0573
  -3.500   0.3272   0.01007   0.00461  -0.1822   0.9274   0.1122
  -3.250   0.3668   0.00960   0.00425  -0.1848   0.9266   0.1544
  -3.000   0.3919   0.00937   0.00413  -0.1842   0.9198   0.1949
  -2.750   0.4291   0.00895   0.00387  -0.1863   0.9175   0.2478
  -2.500   0.4683   0.00860   0.00360  -0.1887   0.9156   0.2905
  -2.250   0.5095   0.00826   0.00334  -0.1915   0.9138   0.3284
  -2.000   0.5413   0.00806   0.00321  -0.1923   0.9082   0.3625
  -1.750   0.5774   0.00784   0.00304  -0.1940   0.9031   0.3979
  -1.500   0.6199   0.00761   0.00286  -0.1971   0.8997   0.4320
  -1.250   0.6519   0.00749   0.00279  -0.1979   0.8921   0.4611
  -1.000   0.6901   0.00733   0.00266  -0.2000   0.8859   0.4917
  -0.750   0.7219   0.00724   0.00262  -0.2008   0.8769   0.5198
  -0.500   0.7603   0.00714   0.00253  -0.2029   0.8693   0.5486
  -0.250   0.7893   0.00711   0.00253  -0.2030   0.8578   0.5744
   0.000   0.8199   0.00709   0.00253  -0.2035   0.8462   0.5996
   0.250   0.8503   0.00709   0.00254  -0.2039   0.8340   0.6245
   0.500   0.8797   0.00711   0.00256  -0.2041   0.8209   0.6495
   0.750   0.9078   0.00715   0.00261  -0.2040   0.8068   0.6736
   1.000   0.9351   0.00722   0.00267  -0.2037   0.7919   0.6977
   1.250   0.9613   0.00730   0.00275  -0.2032   0.7763   0.7209
   1.750   1.0117   0.00751   0.00295  -0.2017   0.7427   0.7681
   2.000   1.0358   0.00764   0.00306  -0.2007   0.7246   0.7919
   2.250   1.0588   0.00779   0.00319  -0.1995   0.7058   0.8154
   2.500   1.0810   0.00794   0.00332  -0.1981   0.6867   0.8399
   2.750   1.1020   0.00809   0.00346  -0.1965   0.6674   0.8661
   3.000   1.1209   0.00823   0.00358  -0.1944   0.6484   0.8953
   3.250   1.1344   0.00829   0.00365  -0.1911   0.6297   0.9411
   3.500   1.1570   0.00847   0.00375  -0.1900   0.6093   1.0000
   3.750   1.1810   0.00875   0.00393  -0.1892   0.5870   1.0000
   4.000   1.2042   0.00906   0.00415  -0.1883   0.5647   1.0000
   4.250   1.2273   0.00936   0.00436  -0.1873   0.5419   1.0000
   4.500   1.2497   0.00970   0.00460  -0.1863   0.5194   1.0000
   4.750   1.2722   0.01003   0.00485  -0.1852   0.4961   1.0000
   5.000   1.2939   0.01041   0.00514  -0.1840   0.4730   1.0000
   5.250   1.3153   0.01079   0.00543  -0.1828   0.4484   1.0000
   5.500   1.3359   0.01120   0.00574  -0.1814   0.4237   1.0000
   5.750   1.3553   0.01166   0.00608  -0.1798   0.3967   1.0000
   6.000   1.3746   0.01215   0.00646  -0.1783   0.3689   1.0000
   6.250   1.3931   0.01269   0.00686  -0.1766   0.3388   1.0000
   6.500   1.4110   0.01329   0.00730  -0.1748   0.3071   1.0000
   6.750   1.4291   0.01389   0.00777  -0.1731   0.2778   1.0000
   7.000   1.4474   0.01450   0.00826  -0.1715   0.2505   1.0000
   7.250   1.4652   0.01514   0.00878  -0.1697   0.2238   1.0000
   7.500   1.4819   0.01584   0.00935  -0.1679   0.1969   1.0000
   7.750   1.4974   0.01663   0.00999  -0.1658   0.1686   1.0000
   8.000   1.5129   0.01742   0.01066  -0.1638   0.1444   1.0000
   8.250   1.5283   0.01822   0.01135  -0.1618   0.1225   1.0000
   8.500   1.5432   0.01904   0.01208  -0.1597   0.1040   1.0000
   8.750   1.5577   0.01988   0.01285  -0.1576   0.0866   1.0000
   9.000   1.5706   0.02085   0.01372  -0.1553   0.0697   1.0000
   9.250   1.5823   0.02190   0.01469  -0.1529   0.0521   1.0000
   9.750   1.5965   0.02478   0.01735  -0.1467   0.0207   1.0000
  10.000   1.6064   0.02601   0.01863  -0.1441   0.0175   1.0000
  10.250   1.6175   0.02715   0.01983  -0.1417   0.0160   1.0000
  10.500   1.6254   0.02856   0.02131  -0.1391   0.0147   1.0000
  10.750   1.6322   0.03008   0.02293  -0.1363   0.0140   1.0000
  11.000   1.6409   0.03146   0.02443  -0.1340   0.0135   1.0000
  11.250   1.6481   0.03300   0.02608  -0.1316   0.0131   1.0000
  11.500   1.6540   0.03468   0.02787  -0.1292   0.0127   1.0000
  11.750   1.6588   0.03650   0.02979  -0.1268   0.0123   1.0000
  12.000   1.6622   0.03852   0.03192  -0.1245   0.0120   1.0000
  12.250   1.6634   0.04082   0.03432  -0.1223   0.0117   1.0000
  12.500   1.6622   0.04345   0.03706  -0.1200   0.0114   1.0000
  12.750   1.6585   0.04647   0.04020  -0.1179   0.0112   1.0000
  13.000   1.6518   0.05001   0.04388  -0.1159   0.0110   1.0000
  13.250   1.6474   0.05347   0.04749  -0.1144   0.0108   1.0000
  13.500   1.6483   0.05640   0.05056  -0.1133   0.0106   1.0000
  13.750   1.6492   0.05944   0.05372  -0.1125   0.0104   1.0000
  14.000   1.6485   0.06280   0.05722  -0.1119   0.0103   1.0000
  14.250   1.6467   0.06642   0.06098  -0.1114   0.0101   1.0000
  14.500   1.6438   0.07032   0.06501  -0.1111   0.0100   1.0000
  14.750   1.6411   0.07429   0.06912  -0.1110   0.0099   1.0000
  15.000   1.6380   0.07844   0.07340  -0.1112   0.0098   1.0000
  15.250   1.6347   0.08270   0.07781  -0.1115   0.0096   1.0000
  15.500   1.6306   0.08719   0.08243  -0.1121   0.0095   1.0000
  15.750   1.6267   0.09175   0.08713  -0.1129   0.0094   1.0000
  16.000   1.6222   0.09648   0.09201  -0.1139   0.0093   1.0000
  16.250   1.6174   0.10135   0.09704  -0.1152   0.0093   1.0000
  16.500   1.6120   0.10640   0.10224  -0.1167   0.0092   1.0000
  16.750   1.6067   0.11151   0.10748  -0.1185   0.0090   1.0000
  17.000   1.6004   0.11685   0.11298  -0.1205   0.0090   1.0000
  17.250   1.5940   0.12233   0.11861  -0.1228   0.0090   1.0000
  17.500   1.5875   0.12790   0.12434  -0.1254   0.0089   1.0000
  17.750   1.5797   0.13385   0.13045  -0.1284   0.0089   1.0000
  18.000   1.5728   0.13963   0.13635  -0.1316   0.0088   1.0000
  18.250   1.5653   0.14566   0.14252  -0.1351   0.0087   1.0000
  18.500   1.5548   0.15256   0.14962  -0.1393   0.0088   1.0000
  18.750   1.5445   0.15959   0.15683  -0.1439   0.0088   1.0000
  19.000   1.5370   0.16600   0.16335  -0.1482   0.0087   1.0000
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