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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 100,000
Max Cl/Cd: 68.84 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e385-il-100000-n5.txt
Download as CSV file: xf-e385-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2734   0.12588   0.12091  -0.0420   1.0000   0.0351
  -9.750  -0.2766   0.12481   0.11990  -0.0427   1.0000   0.0353
  -9.500  -0.2791   0.12333   0.11851  -0.0429   1.0000   0.0354
  -9.250  -0.2818   0.12176   0.11703  -0.0426   1.0000   0.0355
  -9.000  -0.2627   0.11370   0.10896  -0.0396   1.0000   0.0368
  -8.750  -0.2606   0.11105   0.10637  -0.0382   1.0000   0.0375
  -8.500  -0.2621   0.10909   0.10449  -0.0367   1.0000   0.0382
  -8.250  -0.2664   0.10757   0.10305  -0.0349   0.9999   0.0387
  -8.000  -0.2470   0.10365   0.09913  -0.0394   0.9943   0.0401
  -7.750  -0.2286   0.09991   0.09540  -0.0440   0.9875   0.0416
  -7.500  -0.2113   0.09640   0.09188  -0.0486   0.9793   0.0431
  -7.250  -0.1945   0.09309   0.08858  -0.0542   0.9696   0.0450
  -7.000  -0.1798   0.09064   0.08616  -0.0620   0.9545   0.0464
  -6.750  -0.1546   0.08701   0.08252  -0.0729   0.9422   0.0470
  -6.500  -0.1267   0.08271   0.07816  -0.0823   0.9328   0.0472
  -6.250  -0.1134   0.07755   0.07304  -0.0830   0.9247   0.0479
  -6.000  -0.0946   0.07343   0.06891  -0.0834   0.9190   0.0489
  -5.750  -0.0751   0.06999   0.06544  -0.0859   0.9097   0.0500
  -5.500  -0.0472   0.06597   0.06137  -0.0917   0.9030   0.0513
  -5.250  -0.0232   0.06227   0.05762  -0.0970   0.8921   0.0523
  -5.000   0.0223   0.05479   0.04990  -0.1114   0.8819   0.0347
  -4.750   0.0585   0.04812   0.04305  -0.1201   0.8750   0.0280
  -4.500   0.0926   0.04359   0.03829  -0.1260   0.8655   0.0265
  -4.250   0.1361   0.03822   0.03254  -0.1339   0.8597   0.0266
  -4.000   0.1736   0.03370   0.02758  -0.1393   0.8506   0.0267
  -3.750   0.2150   0.02968   0.02305  -0.1444   0.8451   0.0263
  -3.500   0.2507   0.02653   0.01938  -0.1474   0.8364   0.0259
  -3.250   0.2901   0.02371   0.01594  -0.1503   0.8307   0.0259
  -3.000   0.3229   0.02175   0.01346  -0.1516   0.8222   0.0261
  -2.750   0.3578   0.02010   0.01135  -0.1528   0.8162   0.0268
  -2.500   0.3873   0.01899   0.01006  -0.1533   0.8078   0.0286
  -2.250   0.4190   0.01826   0.00917  -0.1540   0.8016   0.0332
  -2.000   0.4480   0.01747   0.00822  -0.1541   0.7934   0.0364
  -1.750   0.4797   0.01677   0.00740  -0.1548   0.7873   0.0429
  -1.500   0.5087   0.01619   0.00682  -0.1550   0.7794   0.0659
  -1.250   0.5394   0.01546   0.00652  -0.1559   0.7733   0.1832
  -1.000   0.5679   0.01499   0.00641  -0.1564   0.7659   0.3317
  -0.750   0.5957   0.01443   0.00638  -0.1564   0.7597   0.5494
  -0.500   0.6076   0.01379   0.00637  -0.1521   0.7529   0.8245
  -0.250   0.6347   0.01372   0.00614  -0.1516   0.7461   1.0000
   0.000   0.6638   0.01388   0.00605  -0.1518   0.7400   1.0000
   0.250   0.6919   0.01406   0.00604  -0.1519   0.7332   1.0000
   0.500   0.7214   0.01421   0.00598  -0.1521   0.7279   1.0000
   0.750   0.7483   0.01444   0.00610  -0.1521   0.7206   1.0000
   1.000   0.7771   0.01460   0.00612  -0.1522   0.7151   1.0000
   1.250   0.8043   0.01483   0.00626  -0.1522   0.7085   1.0000
   1.500   0.8322   0.01504   0.00638  -0.1522   0.7024   1.0000
   1.750   0.8602   0.01525   0.00651  -0.1522   0.6968   1.0000
   2.000   0.8869   0.01550   0.00673  -0.1521   0.6901   1.0000
   2.250   0.9154   0.01569   0.00684  -0.1522   0.6850   1.0000
   2.500   0.9414   0.01597   0.00714  -0.1520   0.6780   1.0000
   2.750   0.9689   0.01619   0.00735  -0.1520   0.6722   1.0000
   3.000   0.9957   0.01646   0.00762  -0.1518   0.6660   1.0000
   3.250   1.0222   0.01672   0.00790  -0.1516   0.6594   1.0000
   3.500   1.0497   0.01694   0.00812  -0.1516   0.6535   1.0000
   3.750   1.0750   0.01724   0.00852  -0.1512   0.6458   1.0000
   4.000   1.1026   0.01743   0.00872  -0.1511   0.6395   1.0000
   4.250   1.1273   0.01772   0.00910  -0.1506   0.6306   1.0000
   4.500   1.1537   0.01793   0.00940  -0.1503   0.6228   1.0000
   4.750   1.1792   0.01816   0.00970  -0.1498   0.6140   1.0000
   5.000   1.2040   0.01841   0.01006  -0.1492   0.6045   1.0000
   5.250   1.2300   0.01858   0.01029  -0.1488   0.5951   1.0000
   5.500   1.2544   0.01879   0.01064  -0.1480   0.5840   1.0000
   5.750   1.2780   0.01903   0.01103  -0.1472   0.5722   1.0000
   6.000   1.3018   0.01925   0.01138  -0.1464   0.5598   1.0000
   6.250   1.3252   0.01947   0.01173  -0.1455   0.5461   1.0000
   6.500   1.3480   0.01969   0.01211  -0.1445   0.5305   1.0000
   6.750   1.3702   0.01992   0.01246  -0.1434   0.5130   1.0000
   7.000   1.3913   0.02021   0.01287  -0.1420   0.4931   1.0000
   7.250   1.4110   0.02055   0.01331  -0.1405   0.4692   1.0000
   7.500   1.4276   0.02100   0.01378  -0.1385   0.4335   1.0000
   7.750   1.4383   0.02178   0.01434  -0.1355   0.3753   1.0000
   8.000   1.4410   0.02320   0.01527  -0.1317   0.3038   1.0000
   8.250   1.4407   0.02497   0.01662  -0.1279   0.2430   1.0000
   8.500   1.4397   0.02673   0.01809  -0.1241   0.1955   1.0000
   8.750   1.4368   0.02862   0.01970  -0.1202   0.1520   1.0000
   9.000   1.4346   0.03060   0.02146  -0.1168   0.1149   1.0000
   9.250   1.4334   0.03266   0.02336  -0.1137   0.0840   1.0000
   9.500   1.4310   0.03498   0.02551  -0.1108   0.0578   1.0000
   9.750   1.4291   0.03741   0.02786  -0.1083   0.0410   1.0000
  10.000   1.4282   0.03990   0.03041  -0.1060   0.0329   1.0000
  10.250   1.4282   0.04242   0.03303  -0.1040   0.0287   1.0000
  10.500   1.4270   0.04518   0.03589  -0.1022   0.0263   1.0000
  10.750   1.4279   0.04781   0.03873  -0.1007   0.0246   1.0000
  11.000   1.4281   0.05061   0.04172  -0.0994   0.0233   1.0000
  11.250   1.4278   0.05356   0.04484  -0.0983   0.0223   1.0000
  11.500   1.4269   0.05665   0.04809  -0.0973   0.0215   1.0000
  11.750   1.4252   0.05994   0.05151  -0.0964   0.0208   1.0000
  12.000   1.4221   0.06348   0.05518  -0.0956   0.0201   1.0000
  12.250   1.4243   0.06647   0.05835  -0.0949   0.0194   1.0000
  12.500   1.4270   0.06948   0.06160  -0.0942   0.0185   1.0000
  12.750   1.4295   0.07258   0.06489  -0.0937   0.0177   1.0000
  13.000   1.4317   0.07577   0.06825  -0.0933   0.0170   1.0000
  13.250   1.4343   0.07902   0.07167  -0.0929   0.0165   1.0000
  13.500   1.4370   0.08237   0.07520  -0.0925   0.0162   1.0000
  13.750   1.4392   0.08584   0.07885  -0.0923   0.0159   1.0000
  14.000   1.4404   0.08952   0.08272  -0.0923   0.0156   1.0000
  14.250   1.4409   0.09342   0.08681  -0.0924   0.0154   1.0000
  14.500   1.4400   0.09760   0.09120  -0.0928   0.0152   1.0000
  14.750   1.4372   0.10216   0.09598  -0.0935   0.0151   1.0000
  15.000   1.4320   0.10721   0.10127  -0.0947   0.0149   1.0000
  15.250   1.4241   0.11278   0.10709  -0.0966   0.0149   1.0000
  15.500   1.4147   0.11870   0.11331  -0.0990   0.0149   1.0000
  15.750   1.4041   0.12503   0.11990  -0.1020   0.0149   1.0000
  16.000   1.3918   0.13198   0.12710  -0.1058   0.0149   1.0000
  16.250   1.3795   0.13918   0.13453  -0.1100   0.0149   1.0000
  16.500   1.3666   0.14695   0.14251  -0.1149   0.0149   1.0000
  16.750   1.3513   0.15582   0.15164  -0.1210   0.0150   1.0000
  17.000   1.3317   0.16711   0.16318  -0.1293   0.0152   1.0000
  17.250   1.2985   0.18509   0.18142  -0.1424   0.0158   1.0000
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