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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 50,000
Max Cl/Cd: 29.34 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e171-il-50000-n5.txt
Download as CSV file: xf-e171-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: (Dicke 12.28%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6914   0.10148   0.09456  -0.0140   1.0000   0.0419
 -12.000  -0.7157   0.09194   0.08499  -0.0202   1.0000   0.0411
 -11.750  -0.7409   0.08376   0.07673  -0.0255   1.0000   0.0403
 -11.500  -0.7668   0.07669   0.06950  -0.0297   1.0000   0.0397
 -11.250  -0.7890   0.07103   0.06367  -0.0324   1.0000   0.0393
 -11.000  -0.8079   0.06629   0.05872  -0.0336   1.0000   0.0392
 -10.750  -0.8232   0.06225   0.05446  -0.0336   1.0000   0.0393
 -10.500  -0.8348   0.05872   0.05068  -0.0327   1.0000   0.0396
 -10.250  -0.8427   0.05551   0.04721  -0.0309   1.0000   0.0401
 -10.000  -0.8456   0.05241   0.04382  -0.0291   1.0000   0.0411
  -9.750  -0.8440   0.04954   0.04060  -0.0275   1.0000   0.0432
  -9.500  -0.8397   0.04675   0.03730  -0.0257   1.0000   0.0458
  -9.250  -0.8269   0.04409   0.03456  -0.0247   1.0000   0.0490
  -9.000  -0.8098   0.04170   0.03192  -0.0237   1.0000   0.0520
  -8.750  -0.7876   0.03929   0.02918  -0.0227   1.0000   0.0562
  -8.500  -0.7703   0.03740   0.02725  -0.0217   1.0000   0.0624
  -8.250  -0.7505   0.03570   0.02528  -0.0205   1.0000   0.0705
  -8.000  -0.7338   0.03392   0.02358  -0.0191   1.0000   0.0777
  -7.750  -0.7202   0.03229   0.02191  -0.0174   1.0000   0.0889
  -7.500  -0.7092   0.03072   0.02039  -0.0155   1.0000   0.1050
  -7.250  -0.6997   0.02911   0.01888  -0.0134   1.0000   0.1261
  -7.000  -0.6919   0.02747   0.01743  -0.0112   1.0000   0.1564
  -6.750  -0.6851   0.02585   0.01613  -0.0088   1.0000   0.2003
  -6.500  -0.6784   0.02435   0.01502  -0.0063   1.0000   0.2573
  -6.250  -0.6706   0.02315   0.01427  -0.0034   1.0000   0.3254
  -6.000  -0.6599   0.02249   0.01401  -0.0003   1.0000   0.3973
  -5.750  -0.6466   0.02226   0.01393   0.0027   1.0000   0.4579
  -5.500  -0.6317   0.02223   0.01390   0.0056   1.0000   0.5034
  -5.250  -0.6162   0.02225   0.01385   0.0083   1.0000   0.5389
  -5.000  -0.6004   0.02226   0.01371   0.0110   1.0000   0.5682
  -4.750  -0.5838   0.02230   0.01366   0.0136   1.0000   0.5927
  -4.500  -0.5689   0.02225   0.01349   0.0161   1.0000   0.6152
  -4.250  -0.5527   0.02227   0.01344   0.0187   1.0000   0.6342
  -4.000  -0.5387   0.02221   0.01329   0.0212   1.0000   0.6524
  -3.750  -0.5262   0.02212   0.01308   0.0238   1.0000   0.6699
  -3.500  -0.5132   0.02205   0.01293   0.0263   1.0000   0.6857
  -3.250  -0.4802   0.02213   0.01281   0.0252   0.9901   0.7019
  -3.000  -0.4420   0.02217   0.01270   0.0231   0.9772   0.7173
  -2.750  -0.4042   0.02217   0.01254   0.0210   0.9648   0.7316
  -2.500  -0.3656   0.02214   0.01233   0.0186   0.9532   0.7451
  -2.250  -0.3269   0.02208   0.01213   0.0163   0.9421   0.7579
  -2.000  -0.2897   0.02200   0.01193   0.0142   0.9308   0.7698
  -1.750  -0.2498   0.02196   0.01178   0.0118   0.9208   0.7799
  -1.500  -0.2100   0.02188   0.01161   0.0093   0.9115   0.7901
  -1.250  -0.1749   0.02178   0.01144   0.0076   0.9006   0.8008
  -1.000  -0.1400   0.02173   0.01131   0.0061   0.8897   0.8108
  -0.750  -0.1030   0.02169   0.01123   0.0042   0.8800   0.8200
  -0.500  -0.0669   0.02162   0.01113   0.0025   0.8706   0.8301
  -0.250  -0.0358   0.02160   0.01108   0.0016   0.8595   0.8406
   0.000   0.0000   0.02161   0.01110   0.0000   0.8496   0.8496
   0.250   0.0358   0.02160   0.01108  -0.0016   0.8407   0.8595
   0.500   0.0669   0.02162   0.01113  -0.0025   0.8301   0.8706
   0.750   0.1030   0.02169   0.01123  -0.0042   0.8200   0.8800
   1.000   0.1400   0.02172   0.01131  -0.0061   0.8108   0.8897
   1.250   0.1748   0.02178   0.01144  -0.0076   0.8008   0.9006
   1.500   0.2099   0.02188   0.01161  -0.0093   0.7901   0.9116
   1.750   0.2497   0.02196   0.01178  -0.0118   0.7799   0.9208
   2.000   0.2896   0.02199   0.01193  -0.0142   0.7699   0.9308
   2.250   0.3269   0.02207   0.01213  -0.0163   0.7579   0.9422
   2.500   0.3655   0.02214   0.01233  -0.0186   0.7452   0.9533
   2.750   0.4041   0.02217   0.01254  -0.0209   0.7317   0.9649
   3.000   0.4420   0.02217   0.01269  -0.0231   0.7173   0.9774
   3.250   0.4802   0.02212   0.01281  -0.0252   0.7019   0.9902
   3.500   0.5129   0.02205   0.01293  -0.0263   0.6858   1.0000
   3.750   0.5259   0.02211   0.01308  -0.0238   0.6700   1.0000
   4.000   0.5384   0.02221   0.01328  -0.0212   0.6524   1.0000
   4.250   0.5524   0.02227   0.01344  -0.0186   0.6342   1.0000
   4.500   0.5687   0.02224   0.01349  -0.0161   0.6152   1.0000
   4.750   0.5836   0.02230   0.01366  -0.0135   0.5927   1.0000
   5.000   0.6002   0.02226   0.01370  -0.0110   0.5682   1.0000
   5.250   0.6160   0.02225   0.01384  -0.0083   0.5389   1.0000
   5.500   0.6316   0.02223   0.01391  -0.0055   0.5035   1.0000
   5.750   0.6464   0.02226   0.01393  -0.0026   0.4578   1.0000
   6.000   0.6598   0.02249   0.01401   0.0004   0.3975   1.0000
   6.250   0.6706   0.02314   0.01427   0.0034   0.3254   1.0000
   6.500   0.6784   0.02435   0.01502   0.0063   0.2572   1.0000
   6.750   0.6852   0.02585   0.01613   0.0088   0.2003   1.0000
   7.000   0.6921   0.02747   0.01743   0.0112   0.1565   1.0000
   7.250   0.6998   0.02911   0.01889   0.0134   0.1260   1.0000
   7.500   0.7095   0.03073   0.02040   0.0154   0.1048   1.0000
   7.750   0.7204   0.03230   0.02192   0.0173   0.0886   1.0000
   8.000   0.7343   0.03392   0.02357   0.0190   0.0779   1.0000
   8.250   0.7511   0.03571   0.02527   0.0204   0.0706   1.0000
   8.500   0.7710   0.03741   0.02726   0.0216   0.0624   1.0000
   8.750   0.7883   0.03931   0.02920   0.0226   0.0562   1.0000
   9.000   0.8104   0.04171   0.03194   0.0236   0.0520   1.0000
   9.250   0.8273   0.04411   0.03457   0.0246   0.0488   1.0000
   9.500   0.8401   0.04677   0.03733   0.0256   0.0458   1.0000
   9.750   0.8447   0.04955   0.04061   0.0273   0.0432   1.0000
  10.000   0.8463   0.05245   0.04386   0.0290   0.0411   1.0000
  10.250   0.8435   0.05555   0.04726   0.0308   0.0402   1.0000
  10.500   0.8354   0.05880   0.05077   0.0325   0.0396   1.0000
  10.750   0.8238   0.06233   0.05453   0.0335   0.0393   1.0000
  11.000   0.8086   0.06636   0.05879   0.0334   0.0392   1.0000
  11.250   0.7896   0.07112   0.06375   0.0322   0.0392   1.0000
  11.500   0.7668   0.07690   0.06973   0.0295   0.0396   1.0000
  11.750   0.7421   0.08380   0.07676   0.0253   0.0402   1.0000
  12.000   0.7146   0.09247   0.08553   0.0196   0.0409   1.0000
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