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FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 200,000
Max Cl/Cd: 70.98 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61168-il-200000.txt
Download as CSV file: xf-fx61168-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4095   0.08762   0.08438  -0.0653   1.0000   0.0532
 -10.250  -0.4330   0.08285   0.07961  -0.0671   1.0000   0.0532
 -10.000  -0.4609   0.07913   0.07589  -0.0673   1.0000   0.0533
  -9.750  -0.4877   0.07672   0.07354  -0.0652   1.0000   0.0532
  -9.500  -0.5019   0.07183   0.06833  -0.0756   0.9844   0.0537
  -9.000  -0.4691   0.05872   0.05528  -0.0837   0.9633   0.0579
  -8.750  -0.4554   0.05461   0.05100  -0.0877   0.9430   0.0607
  -8.500  -0.4535   0.04972   0.04540  -0.0938   0.9218   0.0683
  -8.250  -0.4163   0.04564   0.04142  -0.0977   0.9112   0.0722
  -8.000  -0.3854   0.04143   0.03666  -0.1043   0.8963   0.0831
  -7.750  -0.3437   0.02953   0.02308  -0.1041   0.8849   0.0317
  -7.500  -0.2992   0.02617   0.01929  -0.1079   0.8697   0.0311
  -7.250  -0.2580   0.02446   0.01718  -0.1107   0.8528   0.0324
  -7.000  -0.2227   0.02267   0.01512  -0.1121   0.8372   0.0337
  -6.750  -0.1906   0.02102   0.01340  -0.1124   0.8236   0.0352
  -6.500  -0.1628   0.02010   0.01239  -0.1123   0.8112   0.0368
  -6.250  -0.1394   0.01936   0.01156  -0.1115   0.7998   0.0393
  -6.000  -0.1171   0.01889   0.01098  -0.1107   0.7895   0.0424
  -5.750  -0.0999   0.01784   0.00993  -0.1097   0.7813   0.0473
  -5.500  -0.0813   0.01722   0.00924  -0.1087   0.7723   0.0528
  -5.250  -0.0614   0.01637   0.00833  -0.1084   0.7652   0.0651
  -5.000  -0.0494   0.01403   0.00690  -0.1087   0.7574   0.2303
  -4.750  -0.0271   0.01291   0.00716  -0.1092   0.7518   0.5537
  -4.500  -0.0008   0.01354   0.00775  -0.1081   0.7455   0.5938
  -4.250   0.0254   0.01447   0.00860  -0.1066   0.7398   0.6157
  -4.000   0.0521   0.01558   0.00958  -0.1051   0.7348   0.6367
  -3.750   0.0717   0.01708   0.01115  -0.1008   0.7290   0.6474
  -3.500   0.0952   0.01812   0.01213  -0.0980   0.7241   0.6567
  -3.250   0.1246   0.01812   0.01194  -0.0989   0.7196   0.6673
  -3.000   0.1476   0.01835   0.01214  -0.0973   0.7142   0.6698
  -2.750   0.1732   0.01853   0.01224  -0.0965   0.7095   0.6734
  -2.500   0.2052   0.01833   0.01183  -0.0984   0.7056   0.6826
  -2.250   0.2272   0.01851   0.01202  -0.0968   0.7008   0.6850
  -2.000   0.2518   0.01864   0.01209  -0.0959   0.6961   0.6887
  -1.750   0.2843   0.01841   0.01169  -0.0980   0.6921   0.6974
  -1.500   0.3085   0.01856   0.01181  -0.0969   0.6883   0.6997
  -1.250   0.3313   0.01866   0.01191  -0.0958   0.6834   0.7029
  -1.000   0.3591   0.01863   0.01181  -0.0961   0.6788   0.7087
  -0.750   0.3887   0.01865   0.01171  -0.0967   0.6750   0.7143
  -0.500   0.4095   0.01879   0.01189  -0.0951   0.6701   0.7179
  -0.250   0.4359   0.01879   0.01186  -0.0951   0.6656   0.7231
   0.000   0.4674   0.01868   0.01166  -0.0966   0.6616   0.7285
   0.250   0.4926   0.01877   0.01172  -0.0960   0.6579   0.7311
   0.500   0.5153   0.01882   0.01181  -0.0951   0.6530   0.7347
   0.750   0.5450   0.01878   0.01174  -0.0961   0.6487   0.7397
   1.000   0.5761   0.01875   0.01163  -0.0973   0.6451   0.7438
   1.250   0.5987   0.01884   0.01176  -0.0962   0.6407   0.7464
   1.500   0.6230   0.01887   0.01183  -0.0958   0.6356   0.7499
   1.750   0.6539   0.01885   0.01176  -0.0969   0.6312   0.7541
   2.000   0.6855   0.01886   0.01172  -0.0982   0.6268   0.7583
   2.250   0.7062   0.01890   0.01185  -0.0969   0.6212   0.7608
   2.500   0.7331   0.01891   0.01187  -0.0969   0.6166   0.7637
   2.750   0.7649   0.01897   0.01185  -0.0980   0.6129   0.7672
   3.000   0.7923   0.01903   0.01201  -0.0987   0.6067   0.7719
   3.250   0.8177   0.01903   0.01204  -0.0984   0.6019   0.7744
   3.500   0.8465   0.01907   0.01205  -0.0987   0.5981   0.7768
   3.750   0.8685   0.01917   0.01227  -0.0979   0.5919   0.7799
   4.000   0.8974   0.01917   0.01228  -0.0984   0.5863   0.7836
   4.250   0.9336   0.01919   0.01224  -0.1006   0.5816   0.7873
   4.500   0.9527   0.01922   0.01242  -0.0991   0.5745   0.7896
   4.750   0.9795   0.01919   0.01241  -0.0990   0.5695   0.7921
   5.000   1.0055   0.01926   0.01255  -0.0989   0.5639   0.7952
   5.250   1.0318   0.01927   0.01263  -0.0990   0.5569   0.7987
   5.500   1.0677   0.01920   0.01249  -0.1009   0.5517   0.8018
   5.750   1.0868   0.01921   0.01269  -0.0995   0.5433   0.8043
   6.000   1.1150   0.01906   0.01252  -0.0995   0.5373   0.8070
   6.250   1.1354   0.01909   0.01270  -0.0984   0.5287   0.8101
   6.500   1.1661   0.01896   0.01255  -0.0991   0.5221   0.8130
   6.750   1.1897   0.01901   0.01276  -0.0988   0.5129   0.8163
   7.000   1.2173   0.01891   0.01265  -0.0989   0.5057   0.8190
   7.250   1.2364   0.01890   0.01280  -0.0974   0.4962   0.8217
   7.500   1.2595   0.01889   0.01287  -0.0967   0.4871   0.8244
   7.750   1.2845   0.01889   0.01291  -0.0964   0.4782   0.8276
   8.000   1.3069   0.01900   0.01315  -0.0958   0.4674   0.8309
   8.250   1.3279   0.01905   0.01326  -0.0949   0.4559   0.8337
   8.500   1.3466   0.01911   0.01339  -0.0933   0.4439   0.8363
   8.750   1.3649   0.01925   0.01357  -0.0919   0.4312   0.8394
   9.000   1.3819   0.01947   0.01383  -0.0903   0.4169   0.8430
   9.250   1.3971   0.01980   0.01419  -0.0885   0.4004   0.8465
   9.500   1.4055   0.02012   0.01456  -0.0854   0.3841   0.8494
   9.750   1.4122   0.02057   0.01505  -0.0822   0.3665   0.8527
  10.000   1.4187   0.02121   0.01568  -0.0792   0.3481   0.8566
  10.250   1.4242   0.02204   0.01649  -0.0764   0.3288   0.8608
  10.500   1.4259   0.02294   0.01743  -0.0731   0.3085   0.8647
  10.750   1.4247   0.02410   0.01857  -0.0697   0.2881   0.8688
  11.000   1.4229   0.02558   0.02001  -0.0669   0.2679   0.8732
  11.250   1.4214   0.02726   0.02169  -0.0646   0.2471   0.8776
  11.500   1.4155   0.02919   0.02361  -0.0619   0.2290   0.8826
  11.750   1.4110   0.03139   0.02579  -0.0600   0.2121   0.8884
  12.000   1.4065   0.03371   0.02812  -0.0584   0.1959   0.8943
  12.250   1.4009   0.03623   0.03064  -0.0569   0.1809   0.9008
  12.500   1.3955   0.03893   0.03334  -0.0557   0.1669   0.9078
  12.750   1.3891   0.04162   0.03606  -0.0544   0.1531   0.9168
  13.000   1.3808   0.04442   0.03888  -0.0530   0.1397   0.9297
  13.250   1.3690   0.04712   0.04164  -0.0513   0.1280   1.0000
  13.500   1.3662   0.05073   0.04521  -0.0521   0.1128   1.0000
  13.750   1.3636   0.05439   0.04886  -0.0529   0.0986   1.0000
  14.000   1.3594   0.05830   0.05273  -0.0538   0.0861   1.0000
  14.250   1.3552   0.06231   0.05672  -0.0548   0.0754   1.0000
  14.500   1.3530   0.06618   0.06061  -0.0558   0.0660   1.0000
  14.750   1.3502   0.07016   0.06461  -0.0569   0.0587   1.0000
  15.000   1.3432   0.07477   0.06920  -0.0581   0.0528   1.0000
  15.250   1.3438   0.07847   0.07301  -0.0593   0.0466   1.0000
  15.500   1.3371   0.08321   0.07776  -0.0607   0.0420   1.0000
  15.750   1.3349   0.08742   0.08206  -0.0621   0.0366   1.0000
  16.000   1.3262   0.09266   0.08734  -0.0638   0.0319   1.0000
  16.250   1.3167   0.09815   0.09288  -0.0658   0.0273   1.0000
  16.500   1.3059   0.10391   0.09874  -0.0679   0.0235   1.0000
  16.750   1.2977   0.10938   0.10428  -0.0701   0.0209   1.0000
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