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EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 664 AIRFOIL (e664-il)
Reynolds number: 100,000
Max Cl/Cd: 33.22 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e664-il-100000-n5.txt
Download as CSV file: xf-e664-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 664 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3396   0.09710   0.09217  -0.0849   0.9604   0.0279
 -11.750  -0.3428   0.08920   0.08425  -0.0909   0.9537   0.0275
 -11.500  -0.3593   0.07752   0.07249  -0.1008   0.9472   0.0269
 -11.250  -0.3808   0.06884   0.06362  -0.1084   0.9390   0.0263
 -11.000  -0.4033   0.06187   0.05637  -0.1132   0.9312   0.0260
 -10.750  -0.4201   0.05700   0.05120  -0.1149   0.9222   0.0258
 -10.500  -0.4334   0.05265   0.04650  -0.1154   0.9146   0.0258
 -10.250  -0.4450   0.04951   0.04305  -0.1139   0.9054   0.0256
 -10.000  -0.4529   0.04647   0.03964  -0.1119   0.8982   0.0256
  -9.750  -0.4608   0.04429   0.03715  -0.1085   0.8900   0.0255
  -9.500  -0.4593   0.04186   0.03435  -0.1064   0.8841   0.0256
  -9.250  -0.4521   0.03951   0.03160  -0.1047   0.8797   0.0258
  -9.000  -0.4459   0.03770   0.02948  -0.1022   0.8741   0.0260
  -8.750  -0.4321   0.03580   0.02725  -0.1008   0.8700   0.0263
  -8.500  -0.4121   0.03391   0.02504  -0.1002   0.8669   0.0268
  -8.250  -0.3867   0.03213   0.02294  -0.1003   0.8646   0.0274
  -8.000  -0.3673   0.03092   0.02144  -0.0992   0.8604   0.0283
  -7.750  -0.3478   0.02996   0.02047  -0.0984   0.8564   0.0296
  -7.500  -0.3254   0.02907   0.01951  -0.0980   0.8532   0.0312
  -7.250  -0.2995   0.02808   0.01837  -0.0980   0.8509   0.0330
  -7.000  -0.2730   0.02707   0.01721  -0.0979   0.8489   0.0345
  -6.750  -0.2568   0.02639   0.01655  -0.0965   0.8457   0.0360
  -6.500  -0.2448   0.02595   0.01608  -0.0941   0.8414   0.0380
  -6.250  -0.2290   0.02542   0.01546  -0.0923   0.8378   0.0410
  -6.000  -0.2115   0.02485   0.01489  -0.0910   0.8349   0.0458
  -5.750  -0.1925   0.02424   0.01426  -0.0898   0.8326   0.0540
  -5.500  -0.1789   0.02379   0.01386  -0.0877   0.8297   0.0670
  -5.250  -0.1720   0.02363   0.01378  -0.0844   0.8250   0.0855
  -5.000  -0.1585   0.02321   0.01358  -0.0822   0.8215   0.1219
  -4.750  -0.1436   0.02256   0.01340  -0.0805   0.8187   0.1994
  -4.500  -0.1371   0.02163   0.01322  -0.0774   0.8163   0.3337
  -4.250  -0.0627   0.02336   0.01646  -0.0797   0.8172   0.6450
  -4.000  -0.0661   0.02374   0.01674  -0.0741   0.8134   0.6841
  -3.750  -0.0873   0.02417   0.01717  -0.0659   0.8064   0.7083
  -3.500  -0.0771   0.02470   0.01756  -0.0625   0.8029   0.7339
  -3.250  -0.0628   0.02509   0.01777  -0.0599   0.8003   0.7559
  -3.000  -0.0328   0.02574   0.01825  -0.0593   0.7988   0.7723
  -2.750  -0.0453   0.02659   0.01909  -0.0520   0.7914   0.7843
  -2.500  -0.0223   0.02735   0.01974  -0.0501   0.7883   0.8001
  -2.250   0.0056   0.02802   0.02029  -0.0489   0.7861   0.8174
  -2.000   0.0605   0.02853   0.02063  -0.0527   0.7854   0.8284
  -1.750   0.0951   0.02858   0.02054  -0.0537   0.7838   0.8365
  -1.500   0.1320   0.02849   0.02031  -0.0555   0.7824   0.8417
  -1.250   0.0993   0.02921   0.02109  -0.0450   0.7729   0.8513
  -1.000   0.1258   0.02915   0.02093  -0.0451   0.7701   0.8548
  -0.750   0.1465   0.02899   0.02067  -0.0441   0.7677   0.8593
  -0.500   0.1272   0.02944   0.02114  -0.0362   0.7598   0.8658
  -0.250   0.1420   0.02950   0.02114  -0.0343   0.7553   0.8692
   0.000   0.1652   0.02934   0.02090  -0.0338   0.7527   0.8721
   0.250   0.1891   0.02909   0.02057  -0.0335   0.7506   0.8751
   0.750   0.1816   0.02950   0.02094  -0.0233   0.7367   0.8828
   1.000   0.2135   0.02923   0.02061  -0.0243   0.7348   0.8840
   1.250   0.2473   0.02897   0.02029  -0.0256   0.7331   0.8854
   1.750   0.2420   0.02921   0.02050  -0.0162   0.7185   0.8925
   2.250   0.2615   0.02970   0.02099  -0.0114   0.7046   0.8968
   2.500   0.2947   0.02936   0.02061  -0.0124   0.7026   0.8974
   2.750   0.3307   0.02895   0.02018  -0.0139   0.7012   0.8981
   3.000   0.3173   0.02981   0.02108  -0.0084   0.6884   0.9021
   3.250   0.3516   0.02939   0.02064  -0.0095   0.6865   0.9029
   3.750   0.3811   0.02979   0.02107  -0.0068   0.6721   0.9062
   4.000   0.4168   0.02930   0.02059  -0.0080   0.6704   0.9067
   4.500   0.4511   0.02958   0.02095  -0.0057   0.6557   0.9100
   5.000   0.4897   0.02978   0.02124  -0.0042   0.6412   0.9129
   5.500   0.5317   0.02984   0.02141  -0.0031   0.6265   0.9155
   6.000   0.5764   0.02976   0.02146  -0.0024   0.6117   0.9183
   6.500   0.6235   0.02952   0.02137  -0.0018   0.5964   0.9213
   6.750   0.6387   0.02986   0.02179  -0.0007   0.5850   0.9228
   7.000   0.6735   0.02908   0.02110  -0.0014   0.5805   0.9236
   7.250   0.6901   0.02939   0.02150  -0.0005   0.5683   0.9252
   7.500   0.7142   0.02928   0.02146  -0.0002   0.5581   0.9265
   7.750   0.7481   0.02854   0.02082  -0.0008   0.5501   0.9275
   8.000   0.7701   0.02858   0.02094  -0.0004   0.5368   0.9289
   8.250   0.7959   0.02840   0.02083  -0.0003   0.5235   0.9305
   8.500   0.8239   0.02810   0.02060  -0.0003   0.5092   0.9321
   8.750   0.8513   0.02786   0.02041  -0.0003   0.4931   0.9338
   9.000   0.8771   0.02772   0.02029  -0.0001   0.4750   0.9354
   9.250   0.9031   0.02759   0.02016   0.0001   0.4553   0.9370
   9.500   0.9214   0.02797   0.02055   0.0008   0.4335   0.9388
   9.750   0.9407   0.02832   0.02086   0.0015   0.4108   0.9406
  10.000   0.9568   0.02891   0.02144   0.0024   0.3882   0.9427
  10.250   0.9702   0.02971   0.02221   0.0033   0.3650   0.9449
  10.500   0.9829   0.03059   0.02305   0.0043   0.3428   0.9473
  10.750   0.9936   0.03162   0.02408   0.0053   0.3203   0.9498
  11.000   1.0033   0.03274   0.02515   0.0063   0.2988   0.9528
  11.250   1.0125   0.03398   0.02640   0.0073   0.2773   0.9564
  11.500   1.0210   0.03534   0.02775   0.0080   0.2564   0.9604
  11.750   1.0295   0.03681   0.02920   0.0086   0.2367   0.9648
  12.000   1.0383   0.03835   0.03076   0.0090   0.2174   0.9701
  12.250   1.0457   0.03993   0.03236   0.0094   0.1994   0.9789
  12.500   1.0514   0.04152   0.03396   0.0100   0.1834   1.0000
  12.750   1.0579   0.04341   0.03587   0.0103   0.1677   1.0000
  13.000   1.0631   0.04547   0.03792   0.0106   0.1519   1.0000
  13.250   1.0667   0.04774   0.04016   0.0108   0.1360   1.0000
  13.500   1.0691   0.05023   0.04260   0.0109   0.1203   1.0000
  13.750   1.0715   0.05279   0.04513   0.0108   0.1060   1.0000
  14.000   1.0742   0.05542   0.04776   0.0106   0.0921   1.0000
  14.250   1.0772   0.05811   0.05050   0.0103   0.0819   1.0000
  14.500   1.0807   0.06082   0.05329   0.0099   0.0726   1.0000
  14.750   1.0825   0.06378   0.05632   0.0095   0.0647   1.0000
  15.000   1.0816   0.06714   0.05970   0.0089   0.0582   1.0000
  15.250   1.0815   0.07053   0.06319   0.0081   0.0513   1.0000
  15.500   1.0802   0.07415   0.06689   0.0073   0.0457   1.0000
  15.750   1.0764   0.07818   0.07098   0.0062   0.0418   1.0000
  16.000   1.0745   0.08206   0.07499   0.0050   0.0384   1.0000
  16.250   1.0713   0.08621   0.07925   0.0037   0.0357   1.0000
  16.500   1.0659   0.09074   0.08384   0.0021   0.0340   1.0000
  16.750   1.0648   0.09471   0.08799   0.0007   0.0319   1.0000
  17.000   1.0631   0.09884   0.09225  -0.0009   0.0303   1.0000
  17.250   1.0603   0.10322   0.09672  -0.0029   0.0289   1.0000
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