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FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 100,000
Max Cl/Cd: 48.38 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61168-il-100000-n5.txt
Download as CSV file: xf-fx61168-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-168 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3838   0.09513   0.09029  -0.0582   1.0000   0.0222
 -11.000  -0.4120   0.08400   0.07915  -0.0646   1.0000   0.0213
 -10.750  -0.4696   0.07229   0.06725  -0.0710   1.0000   0.0202
 -10.250  -0.5254   0.06402   0.05870  -0.0708   1.0000   0.0197
 -10.000  -0.5473   0.06157   0.05621  -0.0685   1.0000   0.0197
  -9.750  -0.5516   0.05745   0.05189  -0.0714   0.9901   0.0196
  -9.500  -0.5529   0.05311   0.04722  -0.0745   0.9678   0.0197
  -9.250  -0.5456   0.04904   0.04278  -0.0768   0.9464   0.0197
  -9.000  -0.5342   0.04524   0.03861  -0.0784   0.9280   0.0199
  -8.750  -0.5130   0.04236   0.03555  -0.0806   0.9138   0.0206
  -8.500  -0.4855   0.04007   0.03305  -0.0832   0.9012   0.0218
  -8.250  -0.4550   0.03725   0.02982  -0.0860   0.8894   0.0230
  -8.000  -0.4228   0.03439   0.02649  -0.0883   0.8763   0.0240
  -7.750  -0.3872   0.03186   0.02353  -0.0904   0.8639   0.0247
  -7.500  -0.3493   0.02981   0.02106  -0.0923   0.8520   0.0256
  -7.250  -0.3127   0.02797   0.01920  -0.0942   0.8404   0.0271
  -7.000  -0.2774   0.02680   0.01789  -0.0960   0.8282   0.0295
  -6.750  -0.2458   0.02579   0.01669  -0.0968   0.8155   0.0324
  -6.500  -0.2190   0.02469   0.01554  -0.0968   0.8037   0.0343
  -6.250  -0.1948   0.02380   0.01458  -0.0969   0.7929   0.0373
  -6.000  -0.1698   0.02310   0.01371  -0.0971   0.7833   0.0421
  -5.750  -0.1509   0.02224   0.01282  -0.0965   0.7736   0.0472
  -5.500  -0.1276   0.02147   0.01192  -0.0966   0.7656   0.0558
  -5.250  -0.1081   0.02065   0.01115  -0.0961   0.7569   0.0728
  -5.000  -0.0897   0.01933   0.01023  -0.0961   0.7501   0.1493
  -4.750  -0.0811   0.01737   0.00990  -0.0953   0.7425   0.4439
  -4.500  -0.0559   0.01821   0.01100  -0.0930   0.7371   0.5488
  -4.250  -0.0304   0.01950   0.01222  -0.0909   0.7307   0.5962
  -4.000  -0.0045   0.02081   0.01337  -0.0887   0.7248   0.6234
  -3.750   0.0238   0.02113   0.01345  -0.0885   0.7198   0.6365
  -3.500   0.0483   0.02134   0.01354  -0.0874   0.7139   0.6400
  -3.250   0.0753   0.02140   0.01342  -0.0872   0.7090   0.6455
  -3.000   0.1046   0.02126   0.01305  -0.0881   0.7046   0.6533
  -2.750   0.1283   0.02138   0.01308  -0.0872   0.6990   0.6572
  -2.500   0.1558   0.02131   0.01284  -0.0876   0.6940   0.6638
  -2.250   0.1849   0.02126   0.01262  -0.0881   0.6901   0.6692
  -2.000   0.2080   0.02136   0.01267  -0.0872   0.6847   0.6733
  -1.750   0.2361   0.02128   0.01245  -0.0880   0.6798   0.6813
  -1.500   0.2626   0.02138   0.01244  -0.0875   0.6759   0.6852
  -1.250   0.2872   0.02146   0.01246  -0.0869   0.6714   0.6894
  -1.000   0.3145   0.02138   0.01230  -0.0876   0.6665   0.6957
  -0.750   0.3414   0.02139   0.01222  -0.0877   0.6623   0.6994
  -0.500   0.3689   0.02144   0.01218  -0.0876   0.6588   0.7027
  -0.250   0.3925   0.02149   0.01222  -0.0872   0.6536   0.7070
   0.000   0.4221   0.02143   0.01209  -0.0884   0.6489   0.7126
   0.250   0.4486   0.02147   0.01207  -0.0881   0.6450   0.7152
   0.500   0.4726   0.02155   0.01215  -0.0876   0.6402   0.7184
   0.750   0.4981   0.02160   0.01219  -0.0876   0.6351   0.7224
   1.000   0.5300   0.02158   0.01209  -0.0891   0.6309   0.7274
   1.250   0.5555   0.02165   0.01215  -0.0887   0.6269   0.7297
   1.500   0.5775   0.02178   0.01234  -0.0879   0.6216   0.7328
   1.750   0.6043   0.02185   0.01240  -0.0880   0.6172   0.7363
   2.000   0.6359   0.02188   0.01238  -0.0892   0.6136   0.7402
   2.250   0.6601   0.02203   0.01259  -0.0891   0.6083   0.7436
   2.500   0.6835   0.02215   0.01276  -0.0884   0.6033   0.7462
   2.750   0.7115   0.02220   0.01281  -0.0886   0.5991   0.7493
   3.000   0.7366   0.02235   0.01301  -0.0886   0.5938   0.7527
   3.250   0.7639   0.02248   0.01318  -0.0891   0.5880   0.7565
   3.500   0.7917   0.02252   0.01324  -0.0893   0.5836   0.7592
   3.750   0.8135   0.02271   0.01353  -0.0885   0.5780   0.7620
   4.000   0.8375   0.02286   0.01376  -0.0881   0.5723   0.7650
   4.250   0.8675   0.02291   0.01382  -0.0888   0.5680   0.7683
   4.500   0.8920   0.02317   0.01420  -0.0889   0.5618   0.7721
   4.750   0.9150   0.02330   0.01443  -0.0882   0.5561   0.7746
   5.000   0.9437   0.02330   0.01444  -0.0884   0.5518   0.7772
   5.250   0.9612   0.02361   0.01494  -0.0871   0.5439   0.7804
   5.500   0.9898   0.02364   0.01501  -0.0875   0.5384   0.7838
   5.750   1.0137   0.02390   0.01539  -0.0874   0.5312   0.7872
   6.000   1.0363   0.02400   0.01562  -0.0867   0.5249   0.7897
   6.250   1.0595   0.02413   0.01586  -0.0861   0.5187   0.7925
   6.500   1.0800   0.02431   0.01618  -0.0851   0.5106   0.7958
   6.750   1.1041   0.02442   0.01638  -0.0848   0.5029   0.7991
   7.250   1.1458   0.02474   0.01698  -0.0831   0.4855   0.8051
   7.500   1.1697   0.02471   0.01701  -0.0824   0.4774   0.8082
   7.750   1.1850   0.02504   0.01751  -0.0808   0.4667   0.8117
   8.000   1.2053   0.02526   0.01785  -0.0799   0.4568   0.8151
   8.250   1.2280   0.02538   0.01804  -0.0793   0.4476   0.8182
   8.500   1.2385   0.02576   0.01859  -0.0768   0.4365   0.8215
   8.750   1.2518   0.02608   0.01902  -0.0747   0.4254   0.8253
   9.000   1.2681   0.02642   0.01942  -0.0732   0.4141   0.8292
   9.250   1.2851   0.02680   0.01988  -0.0719   0.4026   0.8329
   9.500   1.2934   0.02745   0.02067  -0.0694   0.3905   0.8364
   9.750   1.3020   0.02816   0.02148  -0.0672   0.3774   0.8406
  10.000   1.3103   0.02900   0.02238  -0.0651   0.3635   0.8454
  10.250   1.3154   0.02995   0.02342  -0.0628   0.3493   0.8499
  10.500   1.3183   0.03110   0.02463  -0.0604   0.3348   0.8548
  10.750   1.3199   0.03253   0.02612  -0.0583   0.3188   0.8600
  11.000   1.3190   0.03414   0.02778  -0.0562   0.3027   0.8651
  11.250   1.3166   0.03598   0.02967  -0.0542   0.2863   0.8711
  11.500   1.3133   0.03811   0.03181  -0.0526   0.2694   0.8778
  11.750   1.3079   0.04041   0.03417  -0.0510   0.2527   0.8856
  12.000   1.3030   0.04283   0.03663  -0.0497   0.2369   0.8949
  12.500   1.2906   0.04781   0.04169  -0.0469   0.2090   0.9270
  12.750   1.2834   0.05050   0.04444  -0.0461   0.1956   1.0000
  13.000   1.2816   0.05376   0.04769  -0.0465   0.1816   1.0000
  13.500   1.2773   0.06059   0.05456  -0.0477   0.1558   1.0000
  13.750   1.2748   0.06420   0.05821  -0.0484   0.1435   1.0000
  14.000   1.2717   0.06797   0.06201  -0.0493   0.1320   1.0000
  14.250   1.2681   0.07188   0.06596  -0.0502   0.1213   1.0000
  14.500   1.2636   0.07602   0.07016  -0.0513   0.1111   1.0000
  14.750   1.2581   0.08040   0.07456  -0.0526   0.1013   1.0000
  15.000   1.2537   0.08475   0.07896  -0.0540   0.0916   1.0000
  15.250   1.2488   0.08927   0.08352  -0.0555   0.0831   1.0000
  15.500   1.2421   0.09412   0.08837  -0.0572   0.0760   1.0000
  15.750   1.2392   0.09853   0.09288  -0.0589   0.0688   1.0000
  16.000   1.2326   0.10354   0.09789  -0.0609   0.0635   1.0000
  16.250   1.2297   0.10809   0.10255  -0.0628   0.0577   1.0000
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