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EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 407 AIRFOIL (e407-il)
Reynolds number: 50,000
Max Cl/Cd: 30.92 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e407-il-50000-n5.txt
Download as CSV file: xf-e407-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 407 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4847   0.11275   0.10605  -0.0481   1.0000   0.0382
 -10.500  -0.5186   0.10101   0.09431  -0.0545   1.0000   0.0360
 -10.250  -0.5338   0.09608   0.08941  -0.0556   1.0000   0.0358
 -10.000  -0.5502   0.09156   0.08496  -0.0563   1.0000   0.0355
  -9.750  -0.5721   0.08691   0.08031  -0.0570   1.0000   0.0353
  -9.500  -0.5931   0.08301   0.07641  -0.0568   1.0000   0.0350
  -9.250  -0.6159   0.07963   0.07300  -0.0559   1.0000   0.0348
  -9.000  -0.6416   0.07665   0.06999  -0.0541   1.0000   0.0346
  -8.750  -0.6660   0.07380   0.06709  -0.0522   1.0000   0.0344
  -8.500  -0.6839   0.07043   0.06359  -0.0514   1.0000   0.0342
  -8.250  -0.6982   0.06673   0.05966  -0.0504   1.0000   0.0343
  -8.000  -0.7062   0.06298   0.05562  -0.0497   1.0000   0.0343
  -7.750  -0.7085   0.05913   0.05141  -0.0492   1.0000   0.0346
  -7.500  -0.7047   0.05539   0.04725  -0.0488   1.0000   0.0348
  -7.250  -0.6956   0.05195   0.04329  -0.0485   1.0000   0.0352
  -7.000  -0.6822   0.04874   0.03956  -0.0480   1.0000   0.0359
  -6.750  -0.6671   0.04582   0.03643  -0.0474   1.0000   0.0371
  -6.500  -0.6509   0.04386   0.03434  -0.0469   1.0000   0.0396
  -6.250  -0.6327   0.04206   0.03228  -0.0461   1.0000   0.0432
  -6.000  -0.6132   0.04035   0.03019  -0.0447   1.0000   0.0467
  -5.750  -0.5909   0.03883   0.02865  -0.0436   0.9982   0.0503
  -5.500  -0.5651   0.03780   0.02740  -0.0432   0.9955   0.0589
  -5.250  -0.5412   0.03667   0.02630  -0.0429   0.9928   0.0677
  -5.000  -0.5167   0.03551   0.02506  -0.0430   0.9897   0.0821
  -4.750  -0.4901   0.03414   0.02378  -0.0442   0.9866   0.1053
  -4.500  -0.4594   0.03227   0.02229  -0.0472   0.9842   0.1574
  -4.250  -0.4279   0.02965   0.02133  -0.0515   0.9824   0.3571
  -4.000  -0.4162   0.03100   0.02335  -0.0458   0.9773   0.5084
  -3.750  -0.3879   0.03234   0.02434  -0.0452   0.9731   0.5767
  -3.500  -0.3670   0.03377   0.02551  -0.0422   0.9687   0.6107
  -3.250  -0.3483   0.03469   0.02621  -0.0394   0.9637   0.6362
  -3.000  -0.3265   0.03555   0.02685  -0.0373   0.9592   0.6575
  -2.750  -0.3037   0.03606   0.02713  -0.0361   0.9548   0.6765
  -2.500  -0.2841   0.03640   0.02729  -0.0341   0.9496   0.6915
  -2.250  -0.2584   0.03676   0.02740  -0.0336   0.9452   0.7056
  -2.000  -0.2384   0.03687   0.02735  -0.0322   0.9399   0.7168
  -1.750  -0.2150   0.03696   0.02727  -0.0315   0.9347   0.7264
  -1.500  -0.1820   0.03708   0.02718  -0.0334   0.9307   0.7356
  -1.250  -0.1614   0.03695   0.02688  -0.0327   0.9244   0.7420
  -1.000  -0.1279   0.03698   0.02672  -0.0350   0.9196   0.7489
  -0.750  -0.1025   0.03697   0.02658  -0.0352   0.9141   0.7538
  -0.500  -0.0735   0.03697   0.02644  -0.0366   0.9082   0.7596
  -0.250  -0.0383   0.03710   0.02641  -0.0389   0.9038   0.7644
   0.000  -0.0170   0.03704   0.02628  -0.0386   0.8965   0.7690
   0.250   0.0181   0.03717   0.02630  -0.0411   0.8914   0.7739
   0.500   0.0451   0.03721   0.02626  -0.0420   0.8845   0.7784
   0.750   0.0754   0.03731   0.02630  -0.0432   0.8784   0.7825
   1.000   0.1047   0.03741   0.02635  -0.0445   0.8715   0.7870
   1.250   0.1381   0.03755   0.02643  -0.0467   0.8649   0.7916
   1.500   0.1647   0.03763   0.02649  -0.0471   0.8576   0.7954
   1.750   0.1966   0.03773   0.02659  -0.0487   0.8506   0.7996
   2.000   0.2263   0.03789   0.02673  -0.0502   0.8425   0.8041
   2.250   0.2593   0.03795   0.02682  -0.0517   0.8358   0.8081
   2.750   0.3227   0.03811   0.02705  -0.0545   0.8206   0.8166
   3.000   0.3470   0.03824   0.02724  -0.0548   0.8100   0.8208
   3.500   0.4099   0.03824   0.02739  -0.0570   0.7934   0.8295
   3.750   0.4364   0.03838   0.02764  -0.0577   0.7821   0.8341
   4.000   0.4619   0.03838   0.02774  -0.0576   0.7715   0.8385
   4.250   0.5008   0.03810   0.02757  -0.0595   0.7644   0.8433
   4.500   0.5275   0.03816   0.02779  -0.0600   0.7521   0.8482
   4.750   0.5516   0.03811   0.02788  -0.0596   0.7397   0.8530
   5.000   0.5794   0.03803   0.02794  -0.0599   0.7275   0.8583
   5.250   0.6088   0.03785   0.02796  -0.0603   0.7154   0.8637
   5.500   0.6388   0.03748   0.02777  -0.0604   0.7038   0.8692
   5.750   0.6765   0.03677   0.02726  -0.0615   0.6936   0.8752
   6.000   0.7033   0.03632   0.02705  -0.0609   0.6797   0.8813
   6.250   0.7331   0.03576   0.02670  -0.0607   0.6654   0.8882
   6.500   0.7628   0.03504   0.02620  -0.0603   0.6506   0.8953
   6.750   0.7860   0.03483   0.02620  -0.0594   0.6311   0.9033
   7.000   0.8146   0.03411   0.02572  -0.0586   0.6126   0.9122
   7.250   0.8500   0.03299   0.02486  -0.0585   0.5931   0.9221
   7.500   0.8771   0.03248   0.02454  -0.0577   0.5671   0.9344
   7.750   0.9103   0.03171   0.02392  -0.0575   0.5370   0.9511
   8.000   0.9388   0.03126   0.02355  -0.0570   0.5009   1.0000
   8.250   0.9689   0.03141   0.02371  -0.0572   0.4592   1.0000
   8.500   0.9919   0.03208   0.02429  -0.0569   0.4153   1.0000
   8.750   1.0096   0.03314   0.02522  -0.0561   0.3720   1.0000
   9.000   1.0238   0.03449   0.02643  -0.0552   0.3304   1.0000
   9.250   1.0356   0.03608   0.02790  -0.0542   0.2909   1.0000
   9.500   1.0456   0.03787   0.02956  -0.0532   0.2538   1.0000
   9.750   1.0549   0.03981   0.03138  -0.0523   0.2204   1.0000
  10.000   1.0632   0.04191   0.03341  -0.0514   0.1905   1.0000
  10.250   1.0718   0.04410   0.03553  -0.0506   0.1639   1.0000
  10.500   1.0804   0.04639   0.03776  -0.0499   0.1412   1.0000
  10.750   1.0885   0.04876   0.04009  -0.0492   0.1224   1.0000
  11.000   1.0975   0.05118   0.04248  -0.0486   0.1074   1.0000
  11.250   1.1078   0.05359   0.04493  -0.0480   0.0945   1.0000
  11.500   1.1183   0.05603   0.04748  -0.0475   0.0831   1.0000
  11.750   1.1326   0.05844   0.05004  -0.0470   0.0744   1.0000
  12.000   1.1413   0.06103   0.05257  -0.0466   0.0676   1.0000
  12.250   1.1541   0.06374   0.05565  -0.0461   0.0609   1.0000
  12.500   1.1665   0.06641   0.05842  -0.0457   0.0565   1.0000
  12.750   1.1753   0.06975   0.06209  -0.0452   0.0524   1.0000
  13.000   1.1767   0.07333   0.06599  -0.0449   0.0488   1.0000
  13.250   1.1778   0.07683   0.06965  -0.0448   0.0462   1.0000
  13.500   1.1843   0.08040   0.07329  -0.0447   0.0442   1.0000
  13.750   1.1770   0.08534   0.07860  -0.0449   0.0432   1.0000
  14.000   1.1637   0.09088   0.08454  -0.0458   0.0424   1.0000
  14.250   1.1476   0.09696   0.09096  -0.0475   0.0419   1.0000
  14.500   1.1293   0.10371   0.09803  -0.0502   0.0415   1.0000
  14.750   1.1093   0.11124   0.10582  -0.0539   0.0415   1.0000
  15.000   1.0878   0.11968   0.11449  -0.0588   0.0418   1.0000
  15.250   1.0659   0.12909   0.12407  -0.0648   0.0422   1.0000
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