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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 100,000
Max Cl/Cd: 45.48 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e432-il-100000-n5.txt
Download as CSV file: xf-e432-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 432 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2467   0.13631   0.13139  -0.0521   1.0000   0.0473
 -12.000  -0.2472   0.13370   0.12885  -0.0521   1.0000   0.0480
 -11.750  -0.2498   0.13127   0.12650  -0.0519   1.0000   0.0488
 -11.500  -0.2427   0.12722   0.12250  -0.0554   0.9961   0.0498
 -11.250  -0.2369   0.12216   0.11746  -0.0620   0.9876   0.0511
 -11.000  -0.2292   0.11713   0.11244  -0.0674   0.9775   0.0513
 -10.750  -0.2158   0.10900   0.10425  -0.0695   0.9692   0.0302
 -10.250  -0.2008   0.09747   0.09273  -0.0783   0.9470   0.0254
 -10.000  -0.1868   0.09331   0.08856  -0.0822   0.9367   0.0249
  -9.750  -0.1747   0.08799   0.08323  -0.0875   0.9277   0.0242
  -9.500  -0.1661   0.08192   0.07714  -0.0937   0.9169   0.0235
  -9.250  -0.1862   0.06642   0.06153  -0.1086   0.9026   0.0213
  -9.000  -0.1857   0.06090   0.05587  -0.1146   0.8881   0.0211
  -8.750  -0.1942   0.05591   0.05067  -0.1184   0.8717   0.0209
  -8.500  -0.2041   0.05244   0.04698  -0.1189   0.8562   0.0208
  -8.250  -0.2112   0.04879   0.04303  -0.1188   0.8435   0.0207
  -8.000  -0.2113   0.04546   0.03935  -0.1185   0.8333   0.0204
  -7.750  -0.2116   0.04237   0.03592  -0.1171   0.8223   0.0203
  -7.500  -0.2055   0.03920   0.03229  -0.1161   0.8140   0.0203
  -7.250  -0.1974   0.03635   0.02898  -0.1146   0.8051   0.0204
  -7.000  -0.1820   0.03370   0.02584  -0.1138   0.7985   0.0206
  -6.750  -0.1666   0.03148   0.02315  -0.1124   0.7905   0.0211
  -6.500  -0.1446   0.02996   0.02136  -0.1121   0.7846   0.0222
  -6.250  -0.1238   0.02888   0.02010  -0.1115   0.7778   0.0236
  -6.000  -0.1008   0.02738   0.01823  -0.1108   0.7715   0.0250
  -5.750  -0.0747   0.02596   0.01655  -0.1105   0.7668   0.0262
  -5.500  -0.0534   0.02500   0.01552  -0.1096   0.7601   0.0274
  -5.250  -0.0292   0.02398   0.01435  -0.1090   0.7547   0.0292
  -5.000  -0.0037   0.02309   0.01335  -0.1087   0.7503   0.0321
  -4.750   0.0171   0.02251   0.01268  -0.1076   0.7440   0.0364
  -4.500   0.0394   0.02180   0.01197  -0.1069   0.7387   0.0409
  -4.250   0.0640   0.02114   0.01125  -0.1065   0.7346   0.0494
  -4.000   0.0850   0.02058   0.01071  -0.1055   0.7293   0.0625
  -3.750   0.1067   0.02004   0.01024  -0.1046   0.7239   0.0854
  -3.500   0.1299   0.01936   0.00978  -0.1041   0.7197   0.1321
  -3.250   0.1511   0.01856   0.00943  -0.1036   0.7156   0.2321
  -3.000   0.1650   0.01748   0.00929  -0.1020   0.7102   0.4341
  -2.750   0.1765   0.01757   0.01022  -0.0970   0.7058   0.6486
  -2.500   0.2009   0.01795   0.01043  -0.0956   0.7020   0.7124
  -2.250   0.2220   0.01837   0.01073  -0.0936   0.6976   0.7451
  -2.000   0.2405   0.01880   0.01107  -0.0910   0.6926   0.7665
  -1.750   0.2612   0.01913   0.01128  -0.0887   0.6885   0.7860
  -1.500   0.2823   0.01945   0.01146  -0.0862   0.6851   0.8079
  -1.250   0.2970   0.01980   0.01176  -0.0827   0.6806   0.8283
  -1.000   0.3131   0.02004   0.01193  -0.0797   0.6759   0.8443
  -0.750   0.3363   0.02009   0.01187  -0.0785   0.6720   0.8528
  -0.500   0.3634   0.02005   0.01166  -0.0785   0.6687   0.8595
  -0.250   0.3846   0.02012   0.01166  -0.0774   0.6642   0.8641
   0.000   0.4057   0.02020   0.01167  -0.0765   0.6593   0.8693
   0.250   0.4310   0.02021   0.01158  -0.0765   0.6555   0.8744
   0.500   0.4599   0.02017   0.01140  -0.0767   0.6523   0.8774
   0.750   0.4808   0.02029   0.01149  -0.0758   0.6478   0.8815
   1.000   0.5017   0.02042   0.01159  -0.0750   0.6430   0.8861
   1.250   0.5278   0.02047   0.01156  -0.0751   0.6391   0.8899
   1.500   0.5572   0.02045   0.01145  -0.0755   0.6361   0.8928
   1.750   0.5775   0.02062   0.01162  -0.0746   0.6314   0.8969
   2.000   0.5979   0.02081   0.01181  -0.0738   0.6265   0.9011
   2.250   0.6244   0.02089   0.01184  -0.0739   0.6226   0.9049
   2.500   0.6543   0.02088   0.01176  -0.0745   0.6196   0.9080
   2.750   0.6724   0.02114   0.01207  -0.0732   0.6146   0.9127
   3.000   0.6930   0.02137   0.01232  -0.0725   0.6096   0.9173
   3.250   0.7205   0.02144   0.01236  -0.0728   0.6059   0.9208
   3.500   0.7521   0.02142   0.01230  -0.0736   0.6029   0.9243
   3.750   0.7651   0.02184   0.01283  -0.0717   0.5969   0.9308
   4.000   0.7881   0.02203   0.01305  -0.0713   0.5921   0.9358
   4.250   0.8186   0.02206   0.01306  -0.0721   0.5886   0.9397
   4.500   0.8456   0.02220   0.01323  -0.0723   0.5845   0.9448
   4.750   0.8615   0.02266   0.01380  -0.0711   0.5780   0.9522
   5.000   0.8919   0.02272   0.01389  -0.0719   0.5737   0.9582
   5.250   0.9296   0.02263   0.01380  -0.0739   0.5705   0.9627
   5.500   0.9451   0.02331   0.01463  -0.0730   0.5629   0.9744
   5.750   0.9781   0.02339   0.01475  -0.0745   0.5580   0.9852
   6.000   1.0159   0.02322   0.01459  -0.0765   0.5544   1.0000
   6.250   1.0194   0.02406   0.01558  -0.0737   0.5462   1.0000
   6.500   1.0494   0.02409   0.01563  -0.0744   0.5413   1.0000
   7.000   1.0874   0.02490   0.01660  -0.0731   0.5284   1.0000
   7.250   1.1238   0.02471   0.01643  -0.0746   0.5238   1.0000
   7.500   1.1262   0.02560   0.01745  -0.0716   0.5154   1.0000
   7.750   1.1563   0.02556   0.01745  -0.0722   0.5096   1.0000
   8.000   1.1653   0.02630   0.01830  -0.0702   0.5017   1.0000
   8.250   1.1891   0.02645   0.01850  -0.0699   0.4947   1.0000
   8.500   1.1998   0.02717   0.01933  -0.0682   0.4866   1.0000
   8.750   1.2217   0.02736   0.01958  -0.0677   0.4789   1.0000
   9.000   1.2274   0.02834   0.02067  -0.0655   0.4698   1.0000
   9.250   1.2541   0.02829   0.02065  -0.0655   0.4620   1.0000
   9.500   1.2525   0.02971   0.02220  -0.0628   0.4514   1.0000
   9.750   1.2687   0.03023   0.02278  -0.0618   0.4422   1.0000
  10.000   1.2816   0.03093   0.02354  -0.0605   0.4319   1.0000
  10.250   1.2826   0.03247   0.02518  -0.0585   0.4206   1.0000
  10.500   1.2921   0.03350   0.02629  -0.0572   0.4092   1.0000
  10.750   1.3059   0.03424   0.02707  -0.0562   0.3978   1.0000
  11.000   1.3136   0.03546   0.02834  -0.0549   0.3852   1.0000
  11.250   1.3155   0.03722   0.03017  -0.0534   0.3720   1.0000
  11.500   1.3197   0.03887   0.03187  -0.0522   0.3586   1.0000
  11.750   1.3243   0.04053   0.03358  -0.0510   0.3450   1.0000
  12.000   1.3287   0.04225   0.03532  -0.0499   0.3309   1.0000
  12.250   1.3326   0.04407   0.03716  -0.0489   0.3169   1.0000
  12.500   1.3359   0.04600   0.03910  -0.0480   0.3028   1.0000
  12.750   1.3389   0.04801   0.04111  -0.0471   0.2890   1.0000
  13.000   1.3409   0.05017   0.04327  -0.0463   0.2752   1.0000
  13.250   1.3426   0.05244   0.04555  -0.0456   0.2618   1.0000
  13.500   1.3427   0.05495   0.04807  -0.0450   0.2484   1.0000
  13.750   1.3420   0.05768   0.05085  -0.0445   0.2356   1.0000
  14.000   1.3412   0.06049   0.05369  -0.0442   0.2230   1.0000
  14.250   1.3406   0.06336   0.05659  -0.0440   0.2111   1.0000
  14.500   1.3398   0.06630   0.05955  -0.0439   0.1997   1.0000
  14.750   1.3385   0.06935   0.06260  -0.0439   0.1887   1.0000
  15.000   1.3367   0.07264   0.06598  -0.0441   0.1778   1.0000
  15.250   1.3347   0.07602   0.06942  -0.0443   0.1673   1.0000
  15.500   1.3326   0.07943   0.07285  -0.0447   0.1577   1.0000
  15.750   1.3300   0.08300   0.07647  -0.0452   0.1484   1.0000
  16.000   1.3276   0.08666   0.08021  -0.0459   0.1393   1.0000
  16.250   1.3249   0.09037   0.08395  -0.0466   0.1311   1.0000
  16.500   1.3216   0.09428   0.08794  -0.0475   0.1229   1.0000
  16.750   1.3190   0.09814   0.09188  -0.0485   0.1154   1.0000
  17.000   1.3150   0.10222   0.09598  -0.0496   0.1085   1.0000
  17.250   1.3125   0.10621   0.10010  -0.0509   0.1016   1.0000
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