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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 1,000,000
Max Cl/Cd: 150.87 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ec863914-il-1000000.txt
Download as CSV file: xf-ec863914-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 AIRFOIL                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.1842   0.12009   0.11814  -0.1177   0.9742   0.0067
 -14.000  -0.1850   0.11359   0.11164  -0.1203   0.9738   0.0067
  -6.500  -0.1333   0.01521   0.01027  -0.1521   0.9097   0.0091
  -6.250  -0.0959   0.01429   0.00924  -0.1547   0.9092   0.0084
  -6.000  -0.0595   0.01369   0.00856  -0.1570   0.9088   0.0084
  -5.750  -0.0227   0.01318   0.00799  -0.1593   0.9085   0.0086
  -5.500   0.0138   0.01277   0.00753  -0.1613   0.9082   0.0084
  -5.250   0.0507   0.01237   0.00709  -0.1635   0.9079   0.0088
  -5.000   0.0876   0.01202   0.00671  -0.1656   0.9077   0.0092
  -4.750   0.1242   0.01176   0.00641  -0.1676   0.9074   0.0090
  -4.500   0.1611   0.01150   0.00612  -0.1696   0.9071   0.0089
  -4.250   0.1978   0.01126   0.00585  -0.1716   0.9068   0.0089
  -4.000   0.2343   0.01101   0.00559  -0.1735   0.9064   0.0090
  -3.750   0.2714   0.01075   0.00531  -0.1755   0.9061   0.0094
  -3.500   0.3110   0.01040   0.00499  -0.1780   0.9057   0.0151
  -3.250   0.3636   0.00912   0.00442  -0.1846   0.9056   0.2105
  -3.000   0.4057   0.00863   0.00406  -0.1878   0.9048   0.2454
  -2.750   0.4507   0.00807   0.00362  -0.1915   0.9036   0.2808
  -2.500   0.4768   0.00778   0.00348  -0.1914   0.8988   0.3198
  -2.250   0.5135   0.00733   0.00323  -0.1936   0.8961   0.3846
  -2.000   0.5537   0.00685   0.00289  -0.1964   0.8935   0.4412
  -1.750   0.5964   0.00629   0.00252  -0.1998   0.8906   0.5138
  -1.500   0.6265   0.00609   0.00254  -0.2005   0.8863   0.5919
  -1.250   0.6554   0.00603   0.00253  -0.2006   0.8823   0.6180
  -1.000   0.6867   0.00595   0.00245  -0.2013   0.8789   0.6314
  -0.750   0.7185   0.00590   0.00239  -0.2020   0.8757   0.6407
  -0.500   0.7425   0.00593   0.00243  -0.2012   0.8697   0.6482
  -0.250   0.7729   0.00587   0.00236  -0.2016   0.8642   0.6541
   0.000   0.7981   0.00590   0.00240  -0.2010   0.8570   0.6597
   0.250   0.8281   0.00588   0.00234  -0.2013   0.8495   0.6652
   0.500   0.8532   0.00589   0.00237  -0.2007   0.8382   0.6691
   0.750   0.8801   0.00591   0.00236  -0.2003   0.8224   0.6726
   1.000   0.9052   0.00600   0.00234  -0.1996   0.7930   0.6761
   1.250   0.9231   0.00634   0.00241  -0.1974   0.7450   0.6793
   1.500   0.9354   0.00679   0.00263  -0.1940   0.6999   0.6822
   1.750   0.9444   0.00723   0.00289  -0.1900   0.6581   0.6849
   2.000   0.9520   0.00770   0.00317  -0.1858   0.6154   0.6879
   2.250   0.9632   0.00823   0.00350  -0.1824   0.5732   0.6918
   2.500   0.9774   0.00875   0.00382  -0.1797   0.5327   0.6957
   2.750   0.9934   0.00922   0.00414  -0.1774   0.4944   0.6991
   3.000   1.0105   0.00970   0.00447  -0.1754   0.4594   0.7024
   3.250   1.0295   0.01015   0.00477  -0.1737   0.4259   0.7054
   3.500   1.0494   0.01060   0.00507  -0.1723   0.3941   0.7082
   3.750   1.0699   0.01103   0.00536  -0.1711   0.3644   0.7112
   4.000   1.0900   0.01143   0.00568  -0.1697   0.3386   0.7143
   4.250   1.1107   0.01184   0.00600  -0.1684   0.3172   0.7172
   4.500   1.1326   0.01219   0.00628  -0.1675   0.2987   0.7192
   4.750   1.1551   0.01253   0.00656  -0.1666   0.2818   0.7205
   5.000   1.1778   0.01287   0.00684  -0.1659   0.2665   0.7215
   5.250   1.2005   0.01321   0.00712  -0.1651   0.2528   0.7226
   5.500   1.2229   0.01357   0.00742  -0.1643   0.2389   0.7235
   5.750   1.2451   0.01396   0.00773  -0.1634   0.2242   0.7244
   6.000   1.2670   0.01433   0.00806  -0.1626   0.2103   0.7257
   6.250   1.2886   0.01470   0.00840  -0.1617   0.2003   0.7268
   6.500   1.3112   0.01501   0.00872  -0.1609   0.1927   0.7279
   6.750   1.3330   0.01538   0.00907  -0.1600   0.1834   0.7289
   7.000   1.3540   0.01582   0.00945  -0.1590   0.1698   0.7299
   7.250   1.3744   0.01631   0.00985  -0.1579   0.1536   0.7310
   7.500   1.3927   0.01697   0.01036  -0.1565   0.1289   0.7321
   7.750   1.3923   0.01919   0.01196  -0.1523   0.0405   0.7332
   8.000   1.4007   0.02083   0.01337  -0.1493   0.0059   0.7343
   8.250   1.4199   0.02145   0.01405  -0.1481   0.0050   0.7356
   8.500   1.4382   0.02214   0.01479  -0.1467   0.0043   0.7368
   8.750   1.4541   0.02305   0.01578  -0.1449   0.0037   0.7379
   9.000   1.4697   0.02398   0.01680  -0.1431   0.0034   0.7388
   9.250   1.4867   0.02475   0.01764  -0.1417   0.0033   0.7401
   9.500   1.5026   0.02560   0.01857  -0.1401   0.0031   0.7412
   9.750   1.5175   0.02651   0.01956  -0.1383   0.0029   0.7424
  10.000   1.5321   0.02745   0.02057  -0.1366   0.0028   0.7435
  10.250   1.5456   0.02847   0.02167  -0.1348   0.0026   0.7447
  10.500   1.5577   0.02960   0.02286  -0.1329   0.0025   0.7460
  10.750   1.5685   0.03086   0.02421  -0.1308   0.0024   0.7472
  11.000   1.5777   0.03225   0.02569  -0.1286   0.0024   0.7485
  11.250   1.5838   0.03392   0.02746  -0.1261   0.0023   0.7498
  11.500   1.5879   0.03578   0.02943  -0.1235   0.0022   0.7511
  11.750   1.5889   0.03795   0.03171  -0.1207   0.0022   0.7523
  12.000   1.5866   0.04050   0.03439  -0.1178   0.0021   0.7534
  12.250   1.5830   0.04327   0.03730  -0.1151   0.0021   0.7547
  12.500   1.5713   0.04703   0.04123  -0.1120   0.0020   0.7558
  12.750   1.5664   0.05027   0.04461  -0.1099   0.0020   0.7569
  13.000   1.5678   0.05295   0.04740  -0.1085   0.0020   0.7581
  13.250   1.5701   0.05564   0.05019  -0.1073   0.0020   0.7594
  13.500   1.5715   0.05854   0.05321  -0.1064   0.0020   0.7607
  13.750   1.5729   0.06156   0.05633  -0.1057   0.0019   0.7621
  14.000   1.5740   0.06474   0.05962  -0.1052   0.0019   0.7635
  14.250   1.5651   0.06941   0.06444  -0.1048   0.0019   0.7646
  14.500   1.5613   0.07359   0.06873  -0.1049   0.0019   0.7658
  14.750   1.5591   0.07768   0.07294  -0.1053   0.0018   0.7670
  15.000   1.5527   0.08259   0.07799  -0.1061   0.0018   0.7681
  15.250   1.5460   0.08772   0.08326  -0.1072   0.0018   0.7693
  15.500   1.5375   0.09329   0.08897  -0.1087   0.0018   0.7704
  15.750   1.5299   0.09890   0.09472  -0.1105   0.0017   0.7715
  16.000   1.5252   0.10418   0.10013  -0.1125   0.0016   0.7727
  16.250   1.5172   0.11011   0.10618  -0.1149   0.0016   0.7739
  16.500   1.5065   0.11657   0.11278  -0.1176   0.0016   0.7749
  16.750   1.5002   0.12242   0.11875  -0.1204   0.0015   0.7761
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