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EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 500,000
Max Cl/Cd: 106.75 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e403-il-500000.txt
Download as CSV file: xf-e403-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 403 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.2284   0.11390   0.11156  -0.0881   0.9748   0.0258
 -13.000  -0.3557   0.11903   0.11658  -0.0813   0.9844   0.0229
 -12.750  -0.3587   0.11615   0.11371  -0.0807   0.9815   0.0234
 -12.500  -0.3584   0.11181   0.10938  -0.0826   0.9798   0.0239
 -12.250  -0.3594   0.10631   0.10390  -0.0857   0.9784   0.0248
  -8.500  -0.5153   0.02801   0.02232  -0.1091   0.9318   0.0171
  -8.250  -0.5155   0.02792   0.02215  -0.1044   0.9261   0.0169
  -8.000  -0.4998   0.02604   0.02021  -0.1024   0.9234   0.0164
  -7.750  -0.4786   0.02455   0.01862  -0.1016   0.9217   0.0162
  -7.500  -0.4543   0.02336   0.01734  -0.1013   0.9204   0.0162
  -7.250  -0.4272   0.02238   0.01628  -0.1016   0.9193   0.0163
  -7.000  -0.3986   0.02149   0.01532  -0.1024   0.9185   0.0165
  -6.750  -0.3687   0.02070   0.01448  -0.1034   0.9177   0.0168
  -6.500  -0.3407   0.01947   0.01321  -0.1047   0.9170   0.0173
  -6.250  -0.3450   0.01916   0.01287  -0.0995   0.9095   0.0176
  -6.000  -0.3181   0.01847   0.01215  -0.1003   0.9074   0.0181
  -5.750  -0.2873   0.01791   0.01157  -0.1018   0.9061   0.0196
  -5.500  -0.2542   0.01738   0.01100  -0.1036   0.9051   0.0207
  -5.250  -0.2194   0.01679   0.01034  -0.1058   0.9044   0.0221
  -5.000  -0.1838   0.01625   0.00978  -0.1080   0.9037   0.0253
  -4.750  -0.1470   0.01565   0.00924  -0.1106   0.9032   0.0432
  -4.500  -0.0992   0.01312   0.00805  -0.1185   0.9034   0.3489
  -4.250  -0.0584   0.01235   0.00789  -0.1224   0.9031   0.5172
  -4.000  -0.0225   0.01234   0.00788  -0.1242   0.9025   0.5471
  -3.750  -0.0126   0.01267   0.00819  -0.1208   0.8963   0.5584
  -3.500   0.0156   0.01281   0.00829  -0.1209   0.8936   0.5759
  -3.250   0.0478   0.01296   0.00842  -0.1217   0.8920   0.5911
  -3.000   0.0806   0.01314   0.00863  -0.1224   0.8908   0.6036
  -2.750   0.1154   0.01318   0.00868  -0.1237   0.8900   0.6110
  -2.500   0.1512   0.01317   0.00864  -0.1252   0.8892   0.6164
  -2.250   0.1896   0.01306   0.00845  -0.1275   0.8887   0.6211
  -2.000   0.2283   0.01285   0.00823  -0.1297   0.8883   0.6238
  -1.750   0.2678   0.01265   0.00802  -0.1321   0.8879   0.6260
  -1.500   0.2736   0.01287   0.00825  -0.1278   0.8794   0.6283
  -1.250   0.3131   0.01260   0.00796  -0.1301   0.8785   0.6310
  -1.000   0.3533   0.01231   0.00765  -0.1327   0.8775   0.6338
  -0.750   0.3944   0.01201   0.00730  -0.1354   0.8766   0.6367
  -0.500   0.4338   0.01166   0.00695  -0.1378   0.8756   0.6389
  -0.250   0.4725   0.01135   0.00666  -0.1399   0.8746   0.6407
   0.000   0.5108   0.01109   0.00641  -0.1420   0.8736   0.6428
   0.250   0.5490   0.01084   0.00618  -0.1441   0.8725   0.6451
   0.500   0.5621   0.01094   0.00631  -0.1412   0.8648   0.6477
   0.750   0.5980   0.01069   0.00605  -0.1429   0.8624   0.6502
   1.000   0.6359   0.01041   0.00576  -0.1450   0.8603   0.6528
   1.250   0.6755   0.01005   0.00542  -0.1473   0.8582   0.6548
   1.500   0.6932   0.01000   0.00543  -0.1452   0.8503   0.6567
   1.750   0.7277   0.00972   0.00519  -0.1464   0.8461   0.6586
   2.000   0.7582   0.00956   0.00506  -0.1469   0.8410   0.6609
   2.250   0.7829   0.00944   0.00498  -0.1462   0.8333   0.6634
   2.500   0.8136   0.00927   0.00482  -0.1468   0.8265   0.6660
   2.750   0.8399   0.00916   0.00472  -0.1464   0.8169   0.6683
   3.000   0.8640   0.00904   0.00464  -0.1456   0.8048   0.6703
   3.250   0.8903   0.00893   0.00455  -0.1451   0.7898   0.6722
   3.500   0.9181   0.00887   0.00448  -0.1450   0.7710   0.6744
   3.750   0.9416   0.00891   0.00448  -0.1440   0.7459   0.6767
   4.000   0.9650   0.00904   0.00449  -0.1430   0.7128   0.6791
   4.250   0.9825   0.00932   0.00459  -0.1409   0.6712   0.6815
   4.500   0.9930   0.00973   0.00478  -0.1373   0.6272   0.6838
   4.750   1.0000   0.01019   0.00505  -0.1332   0.5829   0.6859
   5.000   1.0046   0.01085   0.00546  -0.1287   0.5313   0.6881
   5.250   1.0100   0.01158   0.00594  -0.1245   0.4775   0.6903
   5.500   1.0201   0.01226   0.00639  -0.1214   0.4302   0.6926
   5.750   1.0335   0.01288   0.00683  -0.1190   0.3906   0.6951
   6.000   1.0490   0.01347   0.00726  -0.1170   0.3539   0.6975
   6.250   1.0641   0.01413   0.00772  -0.1150   0.3135   0.6998
   6.500   1.0789   0.01478   0.00820  -0.1131   0.2724   0.7020
   6.750   1.0953   0.01541   0.00870  -0.1114   0.2392   0.7043
   7.000   1.1113   0.01610   0.00923  -0.1097   0.2052   0.7067
   7.250   1.1275   0.01681   0.00978  -0.1081   0.1712   0.7091
   7.500   1.1436   0.01756   0.01037  -0.1065   0.1390   0.7116
   7.750   1.1591   0.01840   0.01103  -0.1049   0.1077   0.7141
   8.000   1.1734   0.01931   0.01175  -0.1031   0.0749   0.7163
   8.250   1.1826   0.02061   0.01278  -0.1006   0.0362   0.7186
   8.500   1.1955   0.02166   0.01376  -0.0985   0.0223   0.7210
   8.750   1.2117   0.02246   0.01459  -0.0969   0.0193   0.7237
   9.000   1.2271   0.02333   0.01552  -0.0953   0.0176   0.7265
   9.250   1.2435   0.02414   0.01640  -0.0938   0.0167   0.7291
   9.500   1.2587   0.02499   0.01734  -0.0923   0.0159   0.7315
   9.750   1.2722   0.02595   0.01838  -0.0905   0.0153   0.7339
  10.000   1.2829   0.02716   0.01968  -0.0884   0.0146   0.7366
  10.250   1.2889   0.02875   0.02137  -0.0858   0.0141   0.7394
  10.500   1.3010   0.02988   0.02259  -0.0841   0.0138   0.7425
  10.750   1.3120   0.03114   0.02394  -0.0823   0.0135   0.7453
  11.000   1.3228   0.03237   0.02529  -0.0805   0.0131   0.7479
  11.250   1.3319   0.03378   0.02681  -0.0787   0.0128   0.7506
  11.500   1.3406   0.03530   0.02844  -0.0768   0.0125   0.7535
  11.750   1.3484   0.03694   0.03017  -0.0750   0.0123   0.7566
  12.000   1.3562   0.03863   0.03195  -0.0734   0.0121   0.7599
  12.250   1.3633   0.04041   0.03384  -0.0717   0.0119   0.7629
  12.500   1.3702   0.04228   0.03583  -0.0702   0.0117   0.7660
  12.750   1.3765   0.04426   0.03793  -0.0687   0.0116   0.7693
  13.000   1.3825   0.04640   0.04016  -0.0673   0.0114   0.7728
  13.250   1.3884   0.04867   0.04254  -0.0660   0.0112   0.7760
  13.500   1.3940   0.05109   0.04509  -0.0648   0.0111   0.7791
  13.750   1.3997   0.05373   0.04786  -0.0637   0.0110   0.7824
  14.000   1.4054   0.05667   0.05097  -0.0626   0.0109   0.7860
  14.250   1.4097   0.05986   0.05433  -0.0617   0.0108   0.7897
  14.500   1.4109   0.06334   0.05803  -0.0608   0.0108   0.7931
  14.750   1.4083   0.06727   0.06219  -0.0600   0.0107   0.7965
  15.000   1.4022   0.07098   0.06611  -0.0595   0.0107   0.8006
  15.250   1.3946   0.07501   0.07035  -0.0595   0.0107   0.8050
  15.500   1.3856   0.07941   0.07497  -0.0598   0.0106   0.8089
  15.750   1.3752   0.08427   0.08007  -0.0606   0.0106   0.8133
  16.000   1.3637   0.08959   0.08561  -0.0619   0.0105   0.8182
  16.250   1.3509   0.09537   0.09161  -0.0639   0.0105   0.8229
  16.500   1.3375   0.10147   0.09793  -0.0664   0.0105   0.8282
  16.750   1.3228   0.10815   0.10483  -0.0695   0.0105   0.8341
  17.000   1.3051   0.11575   0.11265  -0.0733   0.0106   0.8394
  17.250   1.2888   0.12337   0.12048  -0.0778   0.0105   0.8467
  17.500   1.2718   0.13148   0.12880  -0.0828   0.0106   0.8545
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