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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 500,000
Max Cl/Cd: 115.85 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e216-il-500000-n5.txt
Download as CSV file: xf-e216-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2163   0.08410   0.08163  -0.0823   0.9760   0.0080
  -8.750  -0.2197   0.07989   0.07745  -0.0834   0.9701   0.0079
  -8.250  -0.2952   0.03183   0.02881  -0.1372   0.9438   0.0073
  -8.000  -0.2576   0.02515   0.02141  -0.1495   0.9421   0.0075
  -7.750  -0.2302   0.02225   0.01809  -0.1530   0.9382   0.0077
  -7.500  -0.1995   0.02022   0.01571  -0.1557   0.9351   0.0079
  -7.250  -0.1659   0.01868   0.01388  -0.1582   0.9333   0.0081
  -7.000  -0.1316   0.01740   0.01237  -0.1606   0.9319   0.0082
  -6.750  -0.0966   0.01611   0.01089  -0.1630   0.9308   0.0085
  -6.500  -0.0617   0.01507   0.00976  -0.1653   0.9297   0.0090
  -6.250  -0.0263   0.01425   0.00883  -0.1674   0.9288   0.0093
  -6.000   0.0046   0.01352   0.00801  -0.1685   0.9258   0.0096
  -5.750   0.0341   0.01288   0.00729  -0.1692   0.9216   0.0099
  -5.500   0.0684   0.01225   0.00657  -0.1708   0.9193   0.0103
  -5.250   0.1040   0.01165   0.00588  -0.1727   0.9173   0.0107
  -5.000   0.1406   0.01114   0.00529  -0.1747   0.9156   0.0112
  -4.750   0.1792   0.01057   0.00465  -0.1773   0.9143   0.0119
  -4.500   0.2072   0.01026   0.00429  -0.1774   0.9085   0.0128
  -4.250   0.2415   0.00993   0.00390  -0.1788   0.9048   0.0143
  -4.000   0.2798   0.00954   0.00348  -0.1812   0.9021   0.0173
  -3.750   0.3207   0.00911   0.00308  -0.1841   0.8997   0.0310
  -3.500   0.3513   0.00883   0.00287  -0.1848   0.8930   0.0552
  -3.250   0.3905   0.00848   0.00263  -0.1875   0.8884   0.0907
  -3.000   0.4320   0.00816   0.00243  -0.1906   0.8841   0.1347
  -2.750   0.4660   0.00795   0.00231  -0.1921   0.8764   0.1731
  -2.250   0.5389   0.00761   0.00208  -0.1960   0.8606   0.2453
  -2.000   0.5735   0.00750   0.00200  -0.1975   0.8513   0.2799
  -1.750   0.6073   0.00742   0.00193  -0.1988   0.8408   0.3088
  -1.500   0.6378   0.00739   0.00190  -0.1993   0.8287   0.3336
  -1.250   0.6681   0.00737   0.00188  -0.1998   0.8164   0.3593
  -1.000   0.6978   0.00737   0.00188  -0.2002   0.8034   0.3847
  -0.750   0.7266   0.00739   0.00189  -0.2004   0.7895   0.4105
  -0.500   0.7547   0.00744   0.00191  -0.2004   0.7748   0.4347
  -0.250   0.7820   0.00750   0.00195  -0.2002   0.7590   0.4575
   0.000   0.8088   0.00758   0.00201  -0.1999   0.7425   0.4800
   0.250   0.8350   0.00768   0.00208  -0.1995   0.7253   0.5025
   0.500   0.8609   0.00779   0.00216  -0.1990   0.7078   0.5245
   0.750   0.8863   0.00792   0.00225  -0.1984   0.6900   0.5466
   1.250   0.9366   0.00821   0.00249  -0.1972   0.6541   0.5907
   1.500   0.9615   0.00836   0.00262  -0.1965   0.6358   0.6131
   1.750   0.9861   0.00853   0.00276  -0.1958   0.6169   0.6349
   2.000   1.0102   0.00872   0.00293  -0.1950   0.5972   0.6568
   2.250   1.0340   0.00893   0.00310  -0.1941   0.5766   0.6788
   2.500   1.0579   0.00914   0.00328  -0.1933   0.5556   0.7004
   2.750   1.0814   0.00937   0.00347  -0.1924   0.5352   0.7226
   3.000   1.1047   0.00960   0.00369  -0.1914   0.5153   0.7451
   3.250   1.1280   0.00983   0.00390  -0.1905   0.4952   0.7681
   3.500   1.1505   0.01008   0.00412  -0.1894   0.4742   0.7919
   3.750   1.1721   0.01035   0.00437  -0.1881   0.4526   0.8165
   4.000   1.1931   0.01063   0.00462  -0.1866   0.4294   0.8424
   4.500   1.2307   0.01113   0.00508  -0.1828   0.3889   0.9077
   4.750   1.2468   0.01132   0.00525  -0.1803   0.3687   1.0000
   5.000   1.2689   0.01172   0.00555  -0.1793   0.3471   1.0000
   5.250   1.2911   0.01211   0.00586  -0.1783   0.3256   1.0000
   5.500   1.3124   0.01256   0.00621  -0.1771   0.3024   1.0000
   5.750   1.3328   0.01307   0.00659  -0.1758   0.2755   1.0000
   6.000   1.3511   0.01373   0.00706  -0.1742   0.2411   1.0000
   6.250   1.3694   0.01440   0.00754  -0.1726   0.2084   1.0000
   6.500   1.3881   0.01502   0.00803  -0.1711   0.1824   1.0000
   6.750   1.4074   0.01559   0.00851  -0.1696   0.1618   1.0000
   7.000   1.4251   0.01626   0.00906  -0.1679   0.1390   1.0000
   7.250   1.4429   0.01690   0.00961  -0.1663   0.1193   1.0000
   7.500   1.4604   0.01756   0.01020  -0.1646   0.1022   1.0000
   7.750   1.4769   0.01829   0.01084  -0.1627   0.0855   1.0000
   8.000   1.4927   0.01907   0.01153  -0.1608   0.0681   1.0000
   8.250   1.5077   0.01988   0.01227  -0.1588   0.0538   1.0000
   8.500   1.5227   0.02070   0.01303  -0.1567   0.0426   1.0000
   8.750   1.5374   0.02153   0.01384  -0.1547   0.0329   1.0000
   9.000   1.5508   0.02245   0.01474  -0.1525   0.0234   1.0000
   9.250   1.5628   0.02350   0.01575  -0.1501   0.0150   1.0000
   9.500   1.5756   0.02447   0.01674  -0.1479   0.0121   1.0000
   9.750   1.5885   0.02544   0.01776  -0.1458   0.0106   1.0000
  10.000   1.6017   0.02638   0.01878  -0.1437   0.0099   1.0000
  10.250   1.6145   0.02737   0.01985  -0.1417   0.0093   1.0000
  10.500   1.6261   0.02846   0.02102  -0.1395   0.0087   1.0000
  10.750   1.6365   0.02967   0.02231  -0.1373   0.0083   1.0000
  11.000   1.6456   0.03101   0.02374  -0.1351   0.0079   1.0000
  11.250   1.6540   0.03243   0.02525  -0.1328   0.0077   1.0000
  11.500   1.6630   0.03383   0.02677  -0.1307   0.0076   1.0000
  11.750   1.6708   0.03535   0.02840  -0.1286   0.0074   1.0000
  12.000   1.6777   0.03700   0.03015  -0.1266   0.0072   1.0000
  12.250   1.6835   0.03880   0.03206  -0.1246   0.0071   1.0000
  12.500   1.6881   0.04076   0.03413  -0.1226   0.0069   1.0000
  12.750   1.6917   0.04288   0.03637  -0.1208   0.0068   1.0000
  13.000   1.6943   0.04517   0.03878  -0.1190   0.0067   1.0000
  13.250   1.6958   0.04768   0.04141  -0.1174   0.0066   1.0000
  13.500   1.6967   0.05037   0.04422  -0.1160   0.0064   1.0000
  13.750   1.6963   0.05331   0.04728  -0.1148   0.0063   1.0000
  14.000   1.6949   0.05648   0.05059  -0.1138   0.0062   1.0000
  14.250   1.6927   0.05991   0.05414  -0.1131   0.0061   1.0000
  14.500   1.6890   0.06367   0.05802  -0.1126   0.0060   1.0000
  14.750   1.6838   0.06780   0.06229  -0.1124   0.0059   1.0000
  15.000   1.6765   0.07241   0.06702  -0.1126   0.0058   1.0000
  15.250   1.6680   0.07740   0.07216  -0.1131   0.0058   1.0000
  15.500   1.6567   0.08302   0.07792  -0.1141   0.0056   1.0000
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