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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 200,000
Max Cl/Cd: 99.18 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e216-il-200000.txt
Download as CSV file: xf-e216-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3733   0.10910   0.10592  -0.0237   1.0000   0.0451
  -7.750  -0.3772   0.10705   0.10392  -0.0226   1.0000   0.0461
  -7.500  -0.3785   0.10464   0.10154  -0.0227   0.9993   0.0474
  -7.250  -0.3644   0.10058   0.09748  -0.0287   0.9952   0.0496
  -7.000  -0.3649   0.09658   0.09352  -0.0391   0.9866   0.0517
  -6.750  -0.3556   0.08958   0.08655  -0.0508   0.9780   0.0523
  -6.500  -0.3404   0.08679   0.08375  -0.0467   0.9764   0.0536
  -6.250  -0.3247   0.08417   0.08113  -0.0474   0.9712   0.0551
  -6.000  -0.3045   0.08038   0.07734  -0.0521   0.9660   0.0573
  -5.750  -0.2868   0.07527   0.07222  -0.0599   0.9582   0.0606
  -5.500  -0.2423   0.06176   0.05858  -0.0869   0.9526   0.0659
  -5.250  -0.1723   0.03846   0.03398  -0.1194   0.9503   0.0434
  -5.000  -0.1249   0.03297   0.02791  -0.1267   0.9486   0.0386
  -4.750  -0.0583   0.02677   0.02038  -0.1366   0.9512   0.0341
  -4.500  -0.0218   0.02485   0.01810  -0.1388   0.9471   0.0340
  -4.250   0.0185   0.02323   0.01632  -0.1417   0.9446   0.0351
  -4.000   0.0602   0.02209   0.01509  -0.1446   0.9425   0.0371
  -3.750   0.1033   0.02130   0.01417  -0.1477   0.9408   0.0414
  -3.250   0.1832   0.01916   0.01215  -0.1533   0.9333   0.0816
  -3.000   0.2260   0.01844   0.01172  -0.1568   0.9305   0.1614
  -2.750   0.2685   0.01803   0.01153  -0.1601   0.9281   0.2347
  -2.500   0.3060   0.01775   0.01134  -0.1622   0.9242   0.2903
  -2.000   0.3800   0.01720   0.01095  -0.1659   0.9151   0.3857
  -1.750   0.4227   0.01685   0.01068  -0.1687   0.9131   0.4334
  -1.500   0.4499   0.01673   0.01065  -0.1685   0.9048   0.4696
  -1.250   0.4899   0.01639   0.01035  -0.1707   0.9015   0.5114
  -1.000   0.5321   0.01595   0.01001  -0.1732   0.8994   0.5511
  -0.750   0.5605   0.01580   0.00993  -0.1731   0.8915   0.5851
  -0.500   0.5993   0.01537   0.00957  -0.1748   0.8879   0.6219
  -0.250   0.6408   0.01482   0.00910  -0.1770   0.8857   0.6573
   0.000   0.6813   0.01431   0.00867  -0.1790   0.8829   0.6921
   0.250   0.7085   0.01409   0.00853  -0.1784   0.8741   0.7231
   0.500   0.7505   0.01353   0.00804  -0.1806   0.8712   0.7573
   0.750   0.7803   0.01324   0.00783  -0.1804   0.8633   0.7888
   1.000   0.8180   0.01278   0.00743  -0.1817   0.8577   0.8220
   1.250   0.8475   0.01243   0.00715  -0.1814   0.8493   0.8550
   1.500   0.8784   0.01197   0.00672  -0.1812   0.8415   0.8930
   1.750   0.8955   0.01152   0.00634  -0.1783   0.8293   0.9860
   2.000   0.9371   0.01138   0.00614  -0.1811   0.8185   1.0000
   2.250   0.9775   0.01127   0.00596  -0.1836   0.8070   1.0000
   2.500   1.0146   0.01122   0.00586  -0.1853   0.7938   1.0000
   2.750   1.0476   0.01125   0.00583  -0.1862   0.7787   1.0000
   3.000   1.0779   0.01134   0.00586  -0.1865   0.7620   1.0000
   3.250   1.1069   0.01145   0.00594  -0.1866   0.7441   1.0000
   3.500   1.1354   0.01160   0.00602  -0.1865   0.7253   1.0000
   3.750   1.1639   0.01177   0.00611  -0.1865   0.7062   1.0000
   4.000   1.1901   0.01200   0.00627  -0.1860   0.6861   1.0000
   4.250   1.2148   0.01225   0.00648  -0.1852   0.6650   1.0000
   4.500   1.2400   0.01253   0.00667  -0.1845   0.6438   1.0000
   4.750   1.2625   0.01284   0.00693  -0.1833   0.6208   1.0000
   5.000   1.2853   0.01319   0.00720  -0.1821   0.5979   1.0000
   5.250   1.3064   0.01355   0.00751  -0.1807   0.5739   1.0000
   5.500   1.3275   0.01396   0.00784  -0.1792   0.5502   1.0000
   5.750   1.3473   0.01438   0.00820  -0.1776   0.5254   1.0000
   6.000   1.3664   0.01484   0.00861  -0.1758   0.5005   1.0000
   6.250   1.3846   0.01535   0.00903  -0.1739   0.4751   1.0000
   6.500   1.4018   0.01586   0.00949  -0.1718   0.4485   1.0000
   6.750   1.4180   0.01643   0.00999  -0.1696   0.4217   1.0000
   7.000   1.4325   0.01704   0.01052  -0.1671   0.3954   1.0000
   7.250   1.4461   0.01769   0.01110  -0.1645   0.3694   1.0000
   7.500   1.4594   0.01837   0.01172  -0.1618   0.3424   1.0000
   7.750   1.4716   0.01914   0.01240  -0.1591   0.3144   1.0000
   8.000   1.4823   0.02000   0.01315  -0.1561   0.2846   1.0000
   8.250   1.4925   0.02094   0.01398  -0.1533   0.2545   1.0000
   8.500   1.5023   0.02196   0.01489  -0.1504   0.2250   1.0000
   8.750   1.5119   0.02306   0.01586  -0.1477   0.1965   1.0000
   9.000   1.5212   0.02423   0.01692  -0.1449   0.1708   1.0000
   9.250   1.5305   0.02545   0.01806  -0.1423   0.1488   1.0000
   9.500   1.5401   0.02669   0.01926  -0.1398   0.1282   1.0000
   9.750   1.5478   0.02811   0.02061  -0.1371   0.1085   1.0000
  10.000   1.5548   0.02963   0.02207  -0.1345   0.0881   1.0000
  10.250   1.5575   0.03157   0.02390  -0.1315   0.0666   1.0000
  10.500   1.5536   0.03416   0.02634  -0.1278   0.0481   1.0000
  10.750   1.5509   0.03673   0.02893  -0.1244   0.0392   1.0000
  11.000   1.5514   0.03908   0.03140  -0.1215   0.0348   1.0000
  11.250   1.5516   0.04152   0.03393  -0.1190   0.0321   1.0000
  11.500   1.5445   0.04482   0.03727  -0.1162   0.0304   1.0000
  11.750   1.5481   0.04719   0.03983  -0.1143   0.0291   1.0000
  12.000   1.5505   0.04975   0.04254  -0.1125   0.0277   1.0000
  12.250   1.5528   0.05238   0.04528  -0.1110   0.0264   1.0000
  12.500   1.5540   0.05520   0.04817  -0.1096   0.0253   1.0000
  12.750   1.5535   0.05846   0.05149  -0.1082   0.0243   1.0000
  13.000   1.5569   0.06157   0.05471  -0.1068   0.0235   1.0000
  13.250   1.5622   0.06435   0.05767  -0.1057   0.0230   1.0000
  13.500   1.5673   0.06726   0.06076  -0.1047   0.0225   1.0000
  13.750   1.5725   0.07028   0.06397  -0.1038   0.0221   1.0000
  14.000   1.5764   0.07355   0.06743  -0.1030   0.0217   1.0000
  14.250   1.5787   0.07702   0.07113  -0.1024   0.0213   1.0000
  14.500   1.5791   0.08081   0.07514  -0.1019   0.0210   1.0000
  14.750   1.5774   0.08494   0.07950  -0.1017   0.0209   1.0000
  15.000   1.5729   0.08948   0.08429  -0.1019   0.0208   1.0000
  15.250   1.5662   0.09430   0.08936  -0.1024   0.0206   1.0000
  15.500   1.5568   0.09966   0.09498  -0.1035   0.0205   1.0000
  15.750   1.5479   0.10493   0.10046  -0.1050   0.0203   1.0000
  16.000   1.5363   0.11084   0.10661  -0.1072   0.0202   1.0000
  16.250   1.5193   0.11801   0.11407  -0.1104   0.0203   1.0000
  16.500   1.5025   0.12538   0.12169  -0.1142   0.0203   1.0000
  16.750   1.4945   0.13106   0.12751  -0.1174   0.0199   1.0000
  17.000   1.4613   0.14297   0.13981  -0.1253   0.0205   1.0000
  17.250   1.4294   0.15562   0.15279  -0.1343   0.0212   1.0000
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