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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 100,000
Max Cl/Cd: 27.13 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx67k150-il-100000-n5.txt
Download as CSV file: xf-fx67k150-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 67-K-150/17 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1240   0.11861   0.11306  -0.0922   0.8178   0.0343
 -11.250  -0.1217   0.11580   0.11029  -0.0945   0.8152   0.0348
 -11.000  -0.1212   0.11294   0.10746  -0.0971   0.8127   0.0353
 -10.750  -0.1185   0.10982   0.10435  -0.0992   0.8105   0.0354
 -10.500  -0.1163   0.10652   0.10107  -0.1011   0.8086   0.0356
 -10.250  -0.1123   0.10330   0.09786  -0.1029   0.8066   0.0356
 -10.000  -0.1083   0.09993   0.09454  -0.1048   0.8039   0.0356
  -9.750  -0.1053   0.09645   0.09109  -0.1067   0.8013   0.0357
  -9.500  -0.1034   0.09289   0.08756  -0.1087   0.7988   0.0357
  -9.250  -0.0859   0.08987   0.08447  -0.1042   0.7973   0.0416
  -9.000  -0.0843   0.08669   0.08130  -0.1057   0.7952   0.0416
  -8.750  -0.0855   0.08081   0.07541  -0.1092   0.7928   0.0221
  -8.500  -0.0867   0.07694   0.07161  -0.1119   0.7897   0.0223
  -8.250  -0.0888   0.07316   0.06787  -0.1142   0.7866   0.0217
  -8.000  -0.0950   0.06920   0.06390  -0.1169   0.7838   0.0215
  -7.750  -0.1035   0.06630   0.06097  -0.1173   0.7814   0.0201
  -7.500  -0.1129   0.06327   0.05789  -0.1182   0.7775   0.0213
  -7.250  -0.1167   0.06038   0.05492  -0.1183   0.7742   0.0208
  -7.000  -0.1181   0.05741   0.05180  -0.1180   0.7714   0.0206
  -6.750  -0.1164   0.05439   0.04857  -0.1174   0.7690   0.0209
  -6.500  -0.1124   0.05155   0.04550  -0.1166   0.7663   0.0206
  -6.250  -0.1070   0.04906   0.04280  -0.1156   0.7623   0.0205
  -6.000  -0.0987   0.04634   0.03978  -0.1144   0.7595   0.0202
  -5.750  -0.0873   0.04357   0.03667  -0.1131   0.7571   0.0198
  -5.500  -0.0723   0.04095   0.03366  -0.1119   0.7553   0.0195
  -5.250  -0.0585   0.03882   0.03116  -0.1105   0.7519   0.0194
  -5.000  -0.0436   0.03695   0.02893  -0.1089   0.7481   0.0194
  -4.750  -0.0242   0.03507   0.02664  -0.1077   0.7456   0.0196
  -4.500  -0.0019   0.03327   0.02445  -0.1067   0.7437   0.0201
  -4.250   0.0228   0.03160   0.02242  -0.1058   0.7421   0.0209
  -4.000   0.0447   0.03087   0.02139  -0.1048   0.7394   0.0232
  -3.750   0.0595   0.02989   0.02036  -0.1033   0.7348   0.0262
  -3.500   0.0808   0.02895   0.01930  -0.1023   0.7322   0.0285
  -3.250   0.1033   0.02807   0.01832  -0.1013   0.7304   0.0315
  -3.000   0.1261   0.02727   0.01742  -0.1005   0.7288   0.0386
  -2.500   0.1552   0.02714   0.01716  -0.0972   0.7204   0.0533
  -2.250   0.1770   0.02678   0.01673  -0.0964   0.7181   0.0676
  -2.000   0.1946   0.02526   0.01631  -0.0955   0.7164   0.3209
  -1.750   0.1980   0.02426   0.01695  -0.0893   0.7149   0.7383
  -1.500   0.1895   0.02551   0.01828  -0.0832   0.7073   0.8083
  -1.250   0.1933   0.02589   0.01867  -0.0771   0.7045   0.8696
  -1.000   0.2119   0.02601   0.01868  -0.0735   0.7030   0.9167
  -0.750   0.2483   0.02603   0.01846  -0.0749   0.7019   0.9323
  -0.500   0.2618   0.02715   0.01950  -0.0745   0.6950   0.9472
  -0.250   0.2968   0.02749   0.01965  -0.0767   0.6926   0.9574
   0.000   0.3364   0.02765   0.01960  -0.0795   0.6910   0.9657
   0.250   0.3780   0.02773   0.01952  -0.0826   0.6898   0.9721
   0.500   0.4190   0.02776   0.01940  -0.0856   0.6888   0.9784
   0.750   0.4597   0.02778   0.01927  -0.0885   0.6879   0.9839
   1.500   0.4825   0.02986   0.02120  -0.0826   0.6736   1.0000
   2.000   0.4903   0.03140   0.02263  -0.0772   0.6628   1.0000
   2.250   0.5200   0.03145   0.02259  -0.0778   0.6616   1.0000
   2.750   0.5369   0.03341   0.02448  -0.0745   0.6501   1.0000
   3.000   0.5669   0.03348   0.02450  -0.0751   0.6487   1.0000
   3.500   0.5894   0.03540   0.02639  -0.0726   0.6374   1.0000
   3.750   0.6188   0.03549   0.02646  -0.0731   0.6358   1.0000
   4.250   0.6443   0.03736   0.02834  -0.0709   0.6245   1.0000
   4.500   0.6736   0.03743   0.02844  -0.0714   0.6227   1.0000
   4.750   0.7032   0.03747   0.02850  -0.0718   0.6211   1.0000
   5.000   0.7006   0.03927   0.03034  -0.0694   0.6112   1.0000
   5.250   0.7300   0.03929   0.03040  -0.0699   0.6094   1.0000
   5.500   0.7604   0.03924   0.03044  -0.0703   0.6079   1.0000
   5.750   0.7583   0.04107   0.03231  -0.0681   0.5976   1.0000
   6.000   0.7878   0.04104   0.03235  -0.0684   0.5957   1.0000
   6.500   0.8175   0.04271   0.03417  -0.0668   0.5835   1.0000
   6.750   0.8486   0.04246   0.03408  -0.0671   0.5817   1.0000
   7.000   0.8500   0.04417   0.03585  -0.0653   0.5713   1.0000
   7.250   0.8799   0.04394   0.03576  -0.0655   0.5690   1.0000
   7.750   0.9127   0.04531   0.03737  -0.0641   0.5562   1.0000
   8.000   0.9453   0.04476   0.03698  -0.0644   0.5544   1.0000
   8.250   0.9478   0.04642   0.03880  -0.0627   0.5432   1.0000
   8.500   0.9813   0.04562   0.03820  -0.0629   0.5410   1.0000
   8.750   0.9878   0.04682   0.03953  -0.0613   0.5295   1.0000
   9.250   1.0408   0.04510   0.03820  -0.0599   0.5140   1.0000
   9.500   1.0463   0.04583   0.03906  -0.0579   0.4953   1.0000
   9.750   1.0619   0.04515   0.03846  -0.0560   0.4671   1.0000
  10.000   1.1053   0.04074   0.03349  -0.0536   0.3577   1.0000
  10.250   1.0926   0.04326   0.03516  -0.0502   0.2574   1.0000
  10.500   1.0731   0.04712   0.03837  -0.0475   0.1744   1.0000
  10.750   1.0547   0.05112   0.04156  -0.0452   0.0769   1.0000
  11.000   1.0461   0.05442   0.04434  -0.0434   0.0275   1.0000
  11.250   1.0515   0.05657   0.04655  -0.0424   0.0170   1.0000
  11.500   1.0558   0.05887   0.04887  -0.0415   0.0124   1.0000
  11.750   1.0612   0.06113   0.05129  -0.0407   0.0115   1.0000
  12.000   1.0659   0.06354   0.05387  -0.0400   0.0107   1.0000
  12.250   1.0703   0.06603   0.05657  -0.0393   0.0103   1.0000
  12.500   1.0739   0.06863   0.05936  -0.0388   0.0099   1.0000
  12.750   1.0766   0.07140   0.06231  -0.0382   0.0096   1.0000
  13.000   1.0800   0.07410   0.06518  -0.0377   0.0093   1.0000
  13.250   1.0839   0.07674   0.06798  -0.0372   0.0091   1.0000
  13.500   1.0895   0.07918   0.07057  -0.0366   0.0088   1.0000
  13.750   1.0975   0.08132   0.07285  -0.0359   0.0086   1.0000
  14.000   1.1084   0.08318   0.07484  -0.0351   0.0084   1.0000
  14.500   1.1352   0.08674   0.07882  -0.0334   0.0081   1.0000
  14.750   1.1473   0.08899   0.08129  -0.0327   0.0080   1.0000
  15.000   1.1559   0.09181   0.08437  -0.0323   0.0079   1.0000
  15.250   1.1604   0.09523   0.08806  -0.0321   0.0078   1.0000
  15.500   1.1613   0.09906   0.09217  -0.0323   0.0078   1.0000
  15.750   1.1579   0.10350   0.09688  -0.0329   0.0078   1.0000
  16.000   1.1513   0.10842   0.10209  -0.0338   0.0078   1.0000
  16.250   1.1421   0.11377   0.10772  -0.0352   0.0079   1.0000
  16.500   1.1312   0.11949   0.11370  -0.0372   0.0079   1.0000
  16.750   1.1188   0.12563   0.12009  -0.0396   0.0079   1.0000
  17.000   1.1051   0.13232   0.12702  -0.0427   0.0080   1.0000
  17.250   1.0904   0.13951   0.13444  -0.0464   0.0080   1.0000
  17.500   1.0748   0.14736   0.14249  -0.0508   0.0082   1.0000
  17.750   1.0584   0.15594   0.15126  -0.0559   0.0083   1.0000
  18.000   1.0426   0.16514   0.16062  -0.0617   0.0085   1.0000
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