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FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il)
Reynolds number: 100,000
Max Cl/Cd: 16.59 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s161-il-100000.txt
Download as CSV file: xf-fx66s161-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-161 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1656   0.09987   0.09613  -0.0646   0.9450   0.1412
 -10.250  -0.1442   0.09385   0.09004  -0.0687   0.9300   0.1454
 -10.000  -0.2762   0.10479   0.10083  -0.0479   1.0000   0.1348
  -9.750  -0.3113   0.10074   0.09704  -0.0604   0.9714   0.1423
  -9.500  -0.2486   0.09579   0.09197  -0.0585   0.9583   0.1489
  -9.250  -0.1155   0.07569   0.07155  -0.0810   0.8654   0.1741
  -9.000  -0.1018   0.07286   0.06863  -0.0808   0.8511   0.1833
  -8.750  -0.1835   0.07942   0.07533  -0.0811   0.8974   0.1770
  -8.500  -0.1863   0.07491   0.07074  -0.0870   0.8747   0.1889
  -8.250  -0.3355   0.04639   0.04078  -0.1100   0.8544   0.0696
  -8.000  -0.3259   0.04255   0.03663  -0.1099   0.8412   0.0671
  -7.750  -0.3162   0.03895   0.03252  -0.1093   0.8297   0.0646
  -7.500  -0.3022   0.03576   0.02871  -0.1085   0.8202   0.0630
  -7.250  -0.2850   0.03336   0.02584  -0.1075   0.8099   0.0630
  -7.000  -0.2644   0.03167   0.02386  -0.1068   0.8010   0.0658
  -6.750  -0.2423   0.03017   0.02194  -0.1060   0.7928   0.0693
  -6.500  -0.2195   0.02888   0.02024  -0.1050   0.7841   0.0716
  -6.250  -0.1955   0.02681   0.01824  -0.1046   0.7774   0.0771
  -6.000  -0.1720   0.02592   0.01717  -0.1038   0.7698   0.0839
  -5.750  -0.1485   0.02455   0.01588  -0.1030   0.7636   0.0915
  -5.500  -0.1264   0.02362   0.01499  -0.1021   0.7578   0.1032
  -5.250  -0.1064   0.02274   0.01422  -0.1010   0.7514   0.1192
  -5.000  -0.0865   0.02158   0.01323  -0.1000   0.7465   0.1574
  -4.750  -0.0780   0.01985   0.01307  -0.0981   0.7404   0.4084
  -4.500  -0.0546   0.02087   0.01394  -0.0964   0.7346   0.4860
  -4.250  -0.0295   0.02172   0.01469  -0.0947   0.7306   0.5205
  -4.000  -0.0079   0.02243   0.01534  -0.0933   0.7248   0.5461
  -3.750   0.0152   0.02308   0.01599  -0.0914   0.7198   0.5676
  -3.500   0.0398   0.02352   0.01627  -0.0900   0.7159   0.5910
  -3.250   0.0600   0.02409   0.01687  -0.0881   0.7107   0.6084
  -3.000   0.0818   0.02446   0.01721  -0.0866   0.7060   0.6250
  -2.750   0.1065   0.02459   0.01721  -0.0856   0.7022   0.6396
  -2.500   0.1303   0.02474   0.01724  -0.0850   0.6982   0.6527
  -2.250   0.1505   0.02503   0.01753  -0.0841   0.6931   0.6628
  -2.000   0.1749   0.02511   0.01752  -0.0838   0.6894   0.6722
  -1.750   0.2028   0.02508   0.01729  -0.0842   0.6862   0.6824
  -1.500   0.2238   0.02537   0.01758  -0.0834   0.6820   0.6897
  -1.250   0.2455   0.02569   0.01783  -0.0834   0.6770   0.6983
  -1.000   0.2701   0.02582   0.01791  -0.0831   0.6735   0.7057
  -0.750   0.2982   0.02587   0.01783  -0.0834   0.6709   0.7146
  -0.500   0.3168   0.02646   0.01844  -0.0828   0.6668   0.7226
  -0.250   0.3349   0.02708   0.01906  -0.0824   0.6617   0.7305
   0.000   0.3600   0.02728   0.01921  -0.0822   0.6582   0.7389
   0.250   0.3885   0.02733   0.01918  -0.0823   0.6556   0.7476
   0.500   0.3994   0.02852   0.02044  -0.0814   0.6503   0.7570
   0.750   0.4164   0.02916   0.02111  -0.0804   0.6453   0.7659
   1.000   0.4442   0.02922   0.02113  -0.0804   0.6420   0.7769
   1.250   0.4763   0.02911   0.02095  -0.0807   0.6397   0.7889
   1.500   0.4650   0.03149   0.02353  -0.0776   0.6312   0.7995
   1.750   0.4905   0.03167   0.02372  -0.0773   0.6278   0.8122
   2.000   0.5225   0.03150   0.02352  -0.0774   0.6255   0.8265
   2.250   0.4955   0.03506   0.02728  -0.0736   0.6163   0.8424
   2.500   0.5176   0.03547   0.02776  -0.0730   0.6129   0.8637
   2.750   0.5527   0.03506   0.02741  -0.0732   0.6108   0.8924
   3.000   0.5396   0.03935   0.03195  -0.0740   0.6000   1.0000
   3.250   0.5830   0.03949   0.03198  -0.0773   0.5972   1.0000
   3.500   0.6305   0.03916   0.03155  -0.0800   0.5955   1.0000
   3.750   0.5654   0.04576   0.03811  -0.0754   0.5833   1.0000
   4.000   0.6122   0.04531   0.03759  -0.0771   0.5811   1.0000
   4.250   0.5651   0.05081   0.04307  -0.0738   0.5716   1.0000
   4.500   0.5944   0.05141   0.04362  -0.0743   0.5676   1.0000
   4.750   0.6405   0.05098   0.04316  -0.0754   0.5653   1.0000
   5.000   0.5912   0.05673   0.04889  -0.0726   0.5564   1.0000
   5.250   0.6207   0.05733   0.04949  -0.0728   0.5524   1.0000
   5.500   0.6697   0.05672   0.04886  -0.0738   0.5500   1.0000
   5.750   0.6139   0.06323   0.05539  -0.0715   0.5432   1.0000
   6.000   0.5567   0.07208   0.06434  -0.0722   0.5691   1.0000
   6.250   0.5801   0.07385   0.06612  -0.0728   0.5667   1.0000
   6.500   0.6007   0.07606   0.06834  -0.0734   0.5654   1.0000
   6.750   0.6435   0.07227   0.06451  -0.0705   0.5264   1.0000
   7.000   0.7074   0.07050   0.06276  -0.0711   0.5207   1.0000
   7.250   0.6724   0.07587   0.06815  -0.0703   0.5162   1.0000
   7.500   0.6675   0.07924   0.07156  -0.0702   0.5138   1.0000
   7.750   0.6824   0.08112   0.07349  -0.0702   0.5093   1.0000
   8.000   0.6784   0.08482   0.07724  -0.0705   0.5097   1.0000
   8.250   0.6925   0.08725   0.07974  -0.0709   0.5079   1.0000
   8.500   0.7025   0.09013   0.08267  -0.0713   0.5070   1.0000
   8.750   0.7242   0.08924   0.08181  -0.0696   0.4832   1.0000
   9.000   0.7739   0.08804   0.08069  -0.0691   0.4740   1.0000
   9.250   0.7530   0.09252   0.08523  -0.0692   0.4677   1.0000
   9.500   0.8206   0.08982   0.08264  -0.0686   0.4606   1.0000
   9.750   0.7888   0.09503   0.08789  -0.0687   0.4510   1.0000
  10.000   0.8092   0.09609   0.08903  -0.0683   0.4427   1.0000
  10.250   0.8247   0.09756   0.09060  -0.0681   0.4351   1.0000
  10.500   0.8301   0.09993   0.09305  -0.0680   0.4263   1.0000
  10.750   0.8598   0.10009   0.09332  -0.0676   0.4198   1.0000
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