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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 50,000
Max Cl/Cd: 39.17 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e385-il-50000-n5.txt
Download as CSV file: xf-e385-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E385  (8.41%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2768   0.10927   0.10310  -0.0332   1.0000   0.0832
  -7.500  -0.2880   0.10856   0.10252  -0.0309   1.0000   0.0845
  -7.250  -0.3052   0.10856   0.10267  -0.0281   1.0000   0.0859
  -7.000  -0.3120   0.10809   0.10231  -0.0298   0.9949   0.0872
  -6.750  -0.2925   0.10481   0.09907  -0.0403   0.9823   0.0887
  -6.500  -0.2730   0.09925   0.09347  -0.0365   0.9796   0.0931
  -6.250  -0.2527   0.09580   0.08999  -0.0421   0.9699   0.0992
  -6.000  -0.2280   0.09363   0.08779  -0.0592   0.9532   0.1030
  -5.750  -0.2142   0.08841   0.08261  -0.0536   0.9491   0.1061
  -5.500  -0.1945   0.08486   0.07904  -0.0566   0.9406   0.1104
  -5.000  -0.1460   0.07740   0.07152  -0.0716   0.9211   0.1200
  -4.750  -0.1242   0.07374   0.06782  -0.0741   0.9136   0.1228
  -4.500  -0.0651   0.06462   0.05826  -0.0929   0.9054   0.0600
  -4.250  -0.0456   0.06131   0.05494  -0.0939   0.8977   0.0557
  -4.000   0.0148   0.05374   0.04684  -0.1089   0.8918   0.0468
  -3.750   0.0508   0.04965   0.04256  -0.1141   0.8863   0.0455
  -3.500   0.0901   0.04554   0.03813  -0.1200   0.8793   0.0444
  -3.250   0.1440   0.04084   0.03284  -0.1283   0.8758   0.0448
  -3.000   0.1889   0.03736   0.02867  -0.1337   0.8698   0.0463
  -2.750   0.2328   0.03436   0.02502  -0.1379   0.8644   0.0476
  -2.500   0.2766   0.03175   0.02192  -0.1416   0.8607   0.0490
  -2.250   0.3079   0.03024   0.02006  -0.1426   0.8532   0.0512
  -2.000   0.3445   0.02879   0.01822  -0.1441   0.8480   0.0564
  -1.750   0.3780   0.02770   0.01686  -0.1450   0.8422   0.0656
  -1.500   0.4092   0.02684   0.01575  -0.1455   0.8354   0.0786
  -1.250   0.4482   0.02577   0.01468  -0.1475   0.8312   0.1287
  -1.000   0.4785   0.02486   0.01423  -0.1486   0.8235   0.2435
  -0.750   0.5089   0.02344   0.01405  -0.1490   0.8186   0.5778
  -0.500   0.5185   0.02287   0.01386  -0.1444   0.8102   1.0000
  -0.250   0.5514   0.02307   0.01358  -0.1453   0.8041   1.0000
   0.000   0.5804   0.02341   0.01355  -0.1456   0.7973   1.0000
   0.250   0.6097   0.02373   0.01356  -0.1460   0.7905   1.0000
   0.500   0.6414   0.02396   0.01350  -0.1467   0.7850   1.0000
   0.750   0.6662   0.02445   0.01380  -0.1465   0.7770   1.0000
   1.000   0.7001   0.02459   0.01373  -0.1474   0.7725   1.0000
   1.250   0.7213   0.02524   0.01426  -0.1467   0.7636   1.0000
   1.500   0.7536   0.02544   0.01431  -0.1474   0.7587   1.0000
   1.750   0.7752   0.02611   0.01489  -0.1468   0.7503   1.0000
   2.000   0.8057   0.02638   0.01507  -0.1472   0.7449   1.0000
   2.250   0.8284   0.02702   0.01568  -0.1467   0.7372   1.0000
   2.500   0.8568   0.02738   0.01600  -0.1469   0.7311   1.0000
   2.750   0.8812   0.02796   0.01656  -0.1466   0.7240   1.0000
   3.000   0.9069   0.02845   0.01705  -0.1464   0.7171   1.0000
   3.250   0.9336   0.02891   0.01755  -0.1463   0.7108   1.0000
   3.500   0.9563   0.02956   0.01825  -0.1458   0.7030   1.0000
   3.750   0.9847   0.02991   0.01864  -0.1458   0.6971   1.0000
   4.000   1.0053   0.03067   0.01947  -0.1450   0.6883   1.0000
   4.250   1.0317   0.03110   0.02002  -0.1447   0.6815   1.0000
   4.500   1.0544   0.03171   0.02073  -0.1441   0.6731   1.0000
   4.750   1.0764   0.03236   0.02149  -0.1433   0.6645   1.0000
   5.000   1.1050   0.03257   0.02181  -0.1431   0.6572   1.0000
   5.250   1.1232   0.03339   0.02284  -0.1419   0.6468   1.0000
   5.500   1.1588   0.03309   0.02268  -0.1422   0.6406   1.0000
   5.750   1.1745   0.03398   0.02374  -0.1406   0.6289   1.0000
   6.000   1.1940   0.03459   0.02454  -0.1393   0.6178   1.0000
   6.250   1.2213   0.03463   0.02482  -0.1386   0.6079   1.0000
   6.500   1.2512   0.03440   0.02480  -0.1380   0.5975   1.0000
   6.750   1.2708   0.03477   0.02539  -0.1364   0.5842   1.0000
   7.000   1.2919   0.03497   0.02587  -0.1349   0.5704   1.0000
   7.250   1.3141   0.03500   0.02614  -0.1333   0.5558   1.0000
   7.500   1.3375   0.03482   0.02621  -0.1317   0.5401   1.0000
   7.750   1.3532   0.03508   0.02672  -0.1294   0.5218   1.0000
   8.000   1.3667   0.03540   0.02728  -0.1267   0.5013   1.0000
   8.250   1.3833   0.03541   0.02754  -0.1242   0.4789   1.0000
   8.500   1.3956   0.03563   0.02796  -0.1213   0.4531   1.0000
   8.750   1.4021   0.03624   0.02870  -0.1179   0.4238   1.0000
   9.000   1.4052   0.03722   0.02977  -0.1144   0.3897   1.0000
   9.250   1.4080   0.03832   0.03078  -0.1109   0.3486   1.0000
   9.500   1.4059   0.04009   0.03233  -0.1076   0.3047   1.0000
   9.750   1.3991   0.04260   0.03458  -0.1045   0.2634   1.0000
  10.000   1.3892   0.04574   0.03747  -0.1020   0.2256   1.0000
  10.250   1.3782   0.04936   0.04086  -0.1001   0.1888   1.0000
  10.500   1.3662   0.05337   0.04461  -0.0987   0.1555   1.0000
  10.750   1.3556   0.05753   0.04861  -0.0978   0.1244   1.0000
  11.000   1.3462   0.06180   0.05270  -0.0971   0.1000   1.0000
  11.250   1.3382   0.06607   0.05690  -0.0966   0.0823   1.0000
  11.500   1.3312   0.07037   0.06116  -0.0961   0.0696   1.0000
  11.750   1.3262   0.07453   0.06535  -0.0957   0.0604   1.0000
  12.000   1.3215   0.07870   0.06952  -0.0954   0.0549   1.0000
  12.250   1.3219   0.08227   0.07329  -0.0947   0.0497   1.0000
  12.500   1.3215   0.08596   0.07703  -0.0944   0.0463   1.0000
  12.750   1.3264   0.08906   0.08034  -0.0936   0.0428   1.0000
  13.000   1.3315   0.09219   0.08371  -0.0931   0.0396   1.0000
  13.250   1.3344   0.09556   0.08720  -0.0930   0.0372   1.0000
  13.500   1.3415   0.09853   0.09028  -0.0923   0.0352   1.0000
  13.750   1.3507   0.10166   0.09386  -0.0915   0.0339   1.0000
  14.000   1.3543   0.10575   0.09832  -0.0916   0.0330   1.0000
  14.250   1.3527   0.11063   0.10355  -0.0925   0.0324   1.0000
  14.500   1.3468   0.11622   0.10946  -0.0943   0.0321   1.0000
  14.750   1.3376   0.12256   0.11610  -0.0969   0.0319   1.0000
  15.000   1.3253   0.12973   0.12356  -0.1005   0.0318   1.0000
  15.250   1.3109   0.13773   0.13181  -0.1051   0.0319   1.0000
  15.500   1.2950   0.14657   0.14088  -0.1106   0.0321   1.0000
  15.750   1.2781   0.15650   0.15100  -0.1173   0.0325   1.0000
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