Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 200,000
Max Cl/Cd: 73 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61168-il-200000-n5.txt
Download as CSV file: xf-fx61168-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4298   0.08886   0.08530  -0.0586   1.0000   0.0113
 -11.750  -0.4698   0.07608   0.07235  -0.0666   1.0000   0.0114
 -11.500  -0.4752   0.07268   0.06897  -0.0680   1.0000   0.0111
 -11.250  -0.5145   0.06448   0.06053  -0.0718   1.0000   0.0113
 -11.000  -0.5230   0.06165   0.05771  -0.0720   1.0000   0.0111
 -10.750  -0.5475   0.05735   0.05328  -0.0719   1.0000   0.0111
 -10.500  -0.5600   0.05127   0.04686  -0.0764   0.9931   0.0112
 -10.250  -0.5676   0.04660   0.04183  -0.0791   0.9770   0.0113
  -9.750  -0.5678   0.03960   0.03425  -0.0815   0.9270   0.0116
  -9.500  -0.5428   0.03611   0.03042  -0.0856   0.9080   0.0118
  -9.250  -0.5066   0.03293   0.02685  -0.0907   0.8909   0.0121
  -9.000  -0.4616   0.03008   0.02359  -0.0966   0.8721   0.0125
  -8.750  -0.4158   0.02768   0.02081  -0.1018   0.8512   0.0131
  -8.500  -0.3736   0.02576   0.01852  -0.1055   0.8299   0.0138
  -8.250  -0.3384   0.02435   0.01681  -0.1074   0.8091   0.0145
  -8.000  -0.3105   0.02332   0.01555  -0.1080   0.7901   0.0156
  -7.750  -0.2876   0.02259   0.01472  -0.1080   0.7734   0.0166
  -7.500  -0.2659   0.02184   0.01383  -0.1074   0.7593   0.0175
  -7.250  -0.2459   0.02107   0.01293  -0.1065   0.7474   0.0184
  -7.000  -0.2271   0.02037   0.01210  -0.1055   0.7370   0.0190
  -6.750  -0.2101   0.01963   0.01126  -0.1043   0.7274   0.0200
  -6.500  -0.1932   0.01892   0.01046  -0.1034   0.7190   0.0211
  -6.250  -0.1736   0.01840   0.00988  -0.1027   0.7109   0.0234
  -6.000  -0.1528   0.01791   0.00925  -0.1021   0.7041   0.0256
  -5.750  -0.1333   0.01724   0.00855  -0.1016   0.6975   0.0284
  -5.500  -0.1105   0.01678   0.00796  -0.1013   0.6919   0.0323
  -5.250  -0.0876   0.01624   0.00739  -0.1012   0.6867   0.0401
  -5.000  -0.0641   0.01568   0.00685  -0.1011   0.6812   0.0558
  -4.750  -0.0408   0.01485   0.00626  -0.1016   0.6765   0.1161
  -4.500  -0.0175   0.01288   0.00537  -0.1039   0.6717   0.3615
  -4.250   0.0098   0.01235   0.00543  -0.1045   0.6670   0.5041
  -4.000   0.0368   0.01261   0.00582  -0.1039   0.6630   0.5645
  -3.750   0.0643   0.01309   0.00626  -0.1033   0.6593   0.5980
  -3.500   0.0917   0.01349   0.00659  -0.1028   0.6549   0.6157
  -3.250   0.1204   0.01360   0.00657  -0.1030   0.6506   0.6239
  -3.000   0.1485   0.01371   0.00657  -0.1030   0.6467   0.6278
  -2.750   0.1782   0.01376   0.00647  -0.1035   0.6432   0.6334
  -2.500   0.2069   0.01377   0.00639  -0.1038   0.6388   0.6381
  -2.250   0.2344   0.01387   0.00643  -0.1037   0.6348   0.6412
  -2.000   0.2629   0.01394   0.00641  -0.1039   0.6313   0.6452
  -1.750   0.2941   0.01397   0.00626  -0.1049   0.6282   0.6513
  -1.500   0.3207   0.01407   0.00638  -0.1046   0.6243   0.6544
  -1.250   0.3478   0.01419   0.00646  -0.1044   0.6205   0.6580
  -1.000   0.3767   0.01426   0.00646  -0.1048   0.6170   0.6625
  -0.750   0.4077   0.01428   0.00635  -0.1058   0.6137   0.6673
  -0.500   0.4343   0.01434   0.00642  -0.1056   0.6095   0.6694
  -0.250   0.4615   0.01441   0.00648  -0.1055   0.6052   0.6719
   0.000   0.4897   0.01447   0.00650  -0.1057   0.6014   0.6749
   0.250   0.5194   0.01453   0.00648  -0.1063   0.5983   0.6784
   0.500   0.5494   0.01455   0.00646  -0.1071   0.5945   0.6823
   0.750   0.5759   0.01461   0.00657  -0.1069   0.5905   0.6842
   1.000   0.6034   0.01469   0.00664  -0.1069   0.5869   0.6864
   1.250   0.6317   0.01476   0.00669  -0.1072   0.5837   0.6888
   1.500   0.6600   0.01484   0.00676  -0.1075   0.5800   0.6918
   1.750   0.6885   0.01488   0.00683  -0.1079   0.5754   0.6952
   2.000   0.7172   0.01493   0.00686  -0.1083   0.5710   0.6979
   2.250   0.7448   0.01500   0.00692  -0.1084   0.5673   0.6996
   2.500   0.7708   0.01508   0.00707  -0.1082   0.5624   0.7018
   2.750   0.7978   0.01515   0.00719  -0.1082   0.5578   0.7043
   3.000   0.8259   0.01522   0.00726  -0.1084   0.5538   0.7069
   3.250   0.8543   0.01530   0.00736  -0.1088   0.5495   0.7097
   3.500   0.8824   0.01538   0.00750  -0.1092   0.5446   0.7126
   3.750   0.9085   0.01546   0.00763  -0.1090   0.5400   0.7144
   4.000   0.9352   0.01555   0.00775  -0.1089   0.5354   0.7164
   4.250   0.9606   0.01563   0.00793  -0.1086   0.5289   0.7185
   4.500   0.9873   0.01570   0.00803  -0.1086   0.5233   0.7210
   4.750   1.0140   0.01581   0.00821  -0.1086   0.5174   0.7237
   5.000   1.0410   0.01590   0.00836  -0.1088   0.5110   0.7265
   5.250   1.0669   0.01599   0.00849  -0.1086   0.5048   0.7285
   5.500   1.0909   0.01609   0.00871  -0.1080   0.4968   0.7304
   5.750   1.1155   0.01619   0.00886  -0.1076   0.4892   0.7326
   6.000   1.1395   0.01630   0.00904  -0.1071   0.4799   0.7349
   6.250   1.1637   0.01644   0.00924  -0.1066   0.4704   0.7373
   6.500   1.1879   0.01659   0.00943  -0.1062   0.4608   0.7399
   6.750   1.2118   0.01677   0.00967  -0.1058   0.4502   0.7426
   7.000   1.2334   0.01696   0.00994  -0.1048   0.4393   0.7444
   7.250   1.2544   0.01719   0.01021  -0.1038   0.4280   0.7462
   7.500   1.2745   0.01746   0.01052  -0.1026   0.4162   0.7485
   7.750   1.2946   0.01776   0.01088  -0.1015   0.4048   0.7510
   8.000   1.3140   0.01810   0.01127  -0.1003   0.3923   0.7536
   8.250   1.3315   0.01851   0.01169  -0.0988   0.3776   0.7561
   8.750   1.3571   0.01942   0.01266  -0.0942   0.3475   0.7603
   9.000   1.3677   0.02000   0.01325  -0.0916   0.3317   0.7628
   9.250   1.3755   0.02072   0.01397  -0.0888   0.3132   0.7655
   9.500   1.3821   0.02156   0.01479  -0.0859   0.2927   0.7683
   9.750   1.3852   0.02262   0.01579  -0.0828   0.2716   0.7710
  10.000   1.3861   0.02384   0.01697  -0.0797   0.2491   0.7734
  10.250   1.3840   0.02531   0.01840  -0.0765   0.2284   0.7757
  10.500   1.3816   0.02699   0.02006  -0.0737   0.2085   0.7784
  10.750   1.3779   0.02895   0.02198  -0.0713   0.1882   0.7814
  11.000   1.3734   0.03121   0.02419  -0.0692   0.1706   0.7846
  11.250   1.3707   0.03356   0.02650  -0.0677   0.1539   0.7876
  11.500   1.3672   0.03603   0.02897  -0.0663   0.1374   0.7899
  11.750   1.3651   0.03856   0.03150  -0.0652   0.1244   0.7926
  12.000   1.3638   0.04113   0.03409  -0.0644   0.1118   0.7954
  12.250   1.3628   0.04380   0.03677  -0.0638   0.1001   0.7984
  12.500   1.3627   0.04647   0.03948  -0.0634   0.0902   0.8015
  12.750   1.3626   0.04915   0.04221  -0.0629   0.0807   0.8044
  13.000   1.3607   0.05208   0.04517  -0.0626   0.0709   0.8076
  13.250   1.3576   0.05526   0.04836  -0.0624   0.0613   0.8111
  13.500   1.3542   0.05859   0.05172  -0.0624   0.0535   0.8148
  13.750   1.3538   0.06167   0.05487  -0.0625   0.0465   0.8184
  14.000   1.3516   0.06500   0.05825  -0.0626   0.0404   0.8220
  14.250   1.3503   0.06834   0.06165  -0.0630   0.0356   0.8260
  14.500   1.3494   0.07175   0.06513  -0.0634   0.0320   0.8304
  14.750   1.3488   0.07514   0.06863  -0.0639   0.0288   0.8350
  15.000   1.3459   0.07890   0.07246  -0.0646   0.0258   0.8401
  15.250   1.3462   0.08233   0.07602  -0.0652   0.0227   0.8462
  15.500   1.3433   0.08616   0.07995  -0.0660   0.0201   0.8527
  15.750   1.3420   0.08984   0.08377  -0.0668   0.0178   0.8613
  16.000   1.3384   0.09371   0.08776  -0.0675   0.0156   0.8722
  16.250   1.3335   0.09757   0.09176  -0.0681   0.0137   0.8894
  16.500   1.3238   0.10080   0.09515  -0.0675   0.0124   1.0000
<< Back to FX 61-168 AIRFOIL (fx61168-il)

Polar data table (+)

Polar graphs


<< Back to FX 61-168 AIRFOIL (fx61168-il)