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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 100,000
Max Cl/Cd: 62.31 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e64-il-100000-n5.txt
Download as CSV file: xf-e64-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E64  (8.45%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3140   0.08517   0.08059  -0.0355   1.0000   0.0324
  -8.250  -0.3162   0.08200   0.07748  -0.0346   1.0000   0.0315
  -8.000  -0.3924   0.09073   0.08587  -0.0341   1.0000   0.0309
  -7.750  -0.3988   0.08783   0.08305  -0.0333   1.0000   0.0291
  -7.500  -0.4225   0.08330   0.07865  -0.0343   1.0000   0.0252
  -7.250  -0.4260   0.08081   0.07624  -0.0332   1.0000   0.0248
  -7.000  -0.4311   0.07755   0.07304  -0.0338   1.0000   0.0246
  -6.750  -0.4346   0.07395   0.06950  -0.0351   1.0000   0.0243
  -6.500  -0.4356   0.07000   0.06557  -0.0372   1.0000   0.0240
  -6.250  -0.4335   0.06556   0.06112  -0.0399   1.0000   0.0236
  -6.000  -0.4279   0.06042   0.05591  -0.0433   1.0000   0.0233
  -5.750  -0.4031   0.05291   0.04814  -0.0516   0.9967   0.0234
  -5.500  -0.3707   0.04543   0.04020  -0.0598   0.9923   0.0233
  -5.250  -0.3368   0.03921   0.03340  -0.0659   0.9883   0.0229
  -5.000  -0.3005   0.03392   0.02742  -0.0707   0.9854   0.0223
  -4.750  -0.2666   0.03005   0.02288  -0.0735   0.9819   0.0221
  -4.500  -0.2323   0.02709   0.01931  -0.0756   0.9785   0.0221
  -4.250  -0.1971   0.02486   0.01657  -0.0774   0.9755   0.0225
  -4.000  -0.1612   0.02309   0.01444  -0.0791   0.9730   0.0232
  -3.750  -0.1304   0.02174   0.01284  -0.0798   0.9684   0.0243
  -3.500  -0.0972   0.02066   0.01164  -0.0812   0.9643   0.0272
  -3.250  -0.0615   0.01980   0.01065  -0.0830   0.9609   0.0309
  -3.000  -0.0298   0.01897   0.00966  -0.0838   0.9557   0.0343
  -2.750   0.0044   0.01817   0.00875  -0.0852   0.9510   0.0433
  -2.500   0.0410   0.01707   0.00807  -0.0874   0.9477   0.1227
  -2.250   0.0709   0.01613   0.00792  -0.0887   0.9422   0.2992
  -2.000   0.1031   0.01563   0.00778  -0.0898   0.9368   0.4205
  -1.750   0.1384   0.01523   0.00765  -0.0913   0.9330   0.5333
  -1.500   0.1639   0.01495   0.00758  -0.0905   0.9252   0.6278
  -1.250   0.1941   0.01463   0.00748  -0.0903   0.9203   0.7280
  -1.000   0.2154   0.01437   0.00738  -0.0881   0.9123   0.8235
  -0.750   0.2538   0.01399   0.00703  -0.0896   0.9070   1.0000
  -0.500   0.2868   0.01399   0.00683  -0.0907   0.8998   1.0000
  -0.250   0.3228   0.01395   0.00664  -0.0923   0.8934   1.0000
   0.000   0.3567   0.01394   0.00650  -0.0935   0.8863   1.0000
   0.250   0.3912   0.01390   0.00635  -0.0947   0.8790   1.0000
   0.500   0.4230   0.01389   0.00625  -0.0954   0.8705   1.0000
   0.750   0.4586   0.01380   0.00610  -0.0967   0.8634   1.0000
   1.000   0.4884   0.01380   0.00606  -0.0970   0.8530   1.0000
   1.250   0.5216   0.01375   0.00596  -0.0978   0.8440   1.0000
   1.500   0.5553   0.01366   0.00585  -0.0987   0.8344   1.0000
   1.750   0.5850   0.01366   0.00585  -0.0988   0.8222   1.0000
   2.000   0.6155   0.01364   0.00583  -0.0990   0.8095   1.0000
   2.250   0.6462   0.01361   0.00580  -0.0993   0.7959   1.0000
   2.500   0.6769   0.01359   0.00579  -0.0995   0.7810   1.0000
   2.750   0.7074   0.01358   0.00581  -0.0996   0.7649   1.0000
   3.000   0.7381   0.01358   0.00581  -0.0998   0.7476   1.0000
   3.250   0.7656   0.01365   0.00591  -0.0994   0.7269   1.0000
   3.500   0.7945   0.01372   0.00600  -0.0992   0.7053   1.0000
   3.750   0.8214   0.01384   0.00613  -0.0986   0.6805   1.0000
   4.000   0.8481   0.01401   0.00628  -0.0981   0.6540   1.0000
   4.250   0.8740   0.01421   0.00646  -0.0973   0.6248   1.0000
   4.500   0.8990   0.01448   0.00671  -0.0965   0.5923   1.0000
   4.750   0.9228   0.01481   0.00697  -0.0954   0.5565   1.0000
   5.000   0.9456   0.01521   0.00728  -0.0942   0.5175   1.0000
   5.250   0.9673   0.01569   0.00765  -0.0929   0.4756   1.0000
   5.500   0.9879   0.01625   0.00812  -0.0915   0.4319   1.0000
   5.750   1.0076   0.01690   0.00863  -0.0900   0.3867   1.0000
   6.000   1.0264   0.01762   0.00920  -0.0884   0.3391   1.0000
   6.250   1.0437   0.01849   0.00985  -0.0867   0.2877   1.0000
   6.500   1.0599   0.01950   0.01058  -0.0850   0.2320   1.0000
   6.750   1.0757   0.02062   0.01143  -0.0834   0.1770   1.0000
   7.000   1.0920   0.02176   0.01232  -0.0819   0.1319   1.0000
   7.250   1.1080   0.02299   0.01331  -0.0804   0.0896   1.0000
   7.500   1.1227   0.02439   0.01449  -0.0787   0.0568   1.0000
   7.750   1.1371   0.02583   0.01588  -0.0768   0.0391   1.0000
   8.000   1.1508   0.02728   0.01739  -0.0747   0.0326   1.0000
   8.250   1.1645   0.02865   0.01894  -0.0726   0.0291   1.0000
   8.500   1.1752   0.03024   0.02064  -0.0703   0.0269   1.0000
   8.750   1.1859   0.03180   0.02237  -0.0679   0.0256   1.0000
   9.000   1.1966   0.03335   0.02411  -0.0655   0.0245   1.0000
   9.250   1.2079   0.03494   0.02587  -0.0634   0.0232   1.0000
   9.500   1.2188   0.03652   0.02759  -0.0614   0.0218   1.0000
   9.750   1.2283   0.03823   0.02939  -0.0594   0.0207   1.0000
  10.000   1.2369   0.04047   0.03171  -0.0575   0.0198   1.0000
  10.250   1.2492   0.04265   0.03417  -0.0558   0.0194   1.0000
  10.500   1.2603   0.04507   0.03687  -0.0541   0.0191   1.0000
  10.750   1.2688   0.04772   0.03983  -0.0523   0.0187   1.0000
  11.000   1.2737   0.05062   0.04305  -0.0503   0.0185   1.0000
  11.250   1.2743   0.05372   0.04649  -0.0482   0.0183   1.0000
  11.500   1.2708   0.05706   0.05016  -0.0462   0.0182   1.0000
  11.750   1.2635   0.06069   0.05412  -0.0445   0.0181   1.0000
  12.000   1.2528   0.06467   0.05842  -0.0432   0.0180   1.0000
  12.250   1.2395   0.06906   0.06311  -0.0425   0.0180   1.0000
  12.500   1.2238   0.07395   0.06829  -0.0427   0.0180   1.0000
  12.750   1.2061   0.07944   0.07405  -0.0439   0.0181   1.0000
  13.000   1.1869   0.08559   0.08045  -0.0461   0.0181   1.0000
  13.250   1.1665   0.09254   0.08762  -0.0495   0.0182   1.0000
  13.500   1.1451   0.10042   0.09571  -0.0542   0.0183   1.0000
  13.750   1.1229   0.10938   0.10485  -0.0600   0.0185   1.0000
  14.000   1.0999   0.11969   0.11531  -0.0671   0.0187   1.0000
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