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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.83 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx67k150-il-1000000-n5.txt
Download as CSV file: xf-fx67k150-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1547   0.04517   0.04208  -0.1144   0.6886   0.0022
  -7.250  -0.1550   0.04115   0.03790  -0.1137   0.6870   0.0022
  -7.000  -0.1521   0.03696   0.03352  -0.1126   0.6853   0.0021
  -6.750  -0.1460   0.03271   0.02904  -0.1112   0.6835   0.0020
  -6.500  -0.1374   0.02824   0.02425  -0.1094   0.6816   0.0020
  -6.250  -0.1291   0.02249   0.01800  -0.1067   0.6798   0.0019
  -6.000  -0.1220   0.01471   0.00925  -0.1028   0.6782   0.0018
  -5.750  -0.0986   0.01327   0.00754  -0.1022   0.6766   0.0018
  -5.500  -0.0740   0.01238   0.00646  -0.1019   0.6750   0.0018
  -5.250  -0.0488   0.01164   0.00559  -0.1016   0.6736   0.0019
  -5.000  -0.0230   0.01104   0.00489  -0.1015   0.6719   0.0020
  -4.750   0.0034   0.01059   0.00435  -0.1014   0.6701   0.0021
  -4.500   0.0302   0.01022   0.00392  -0.1015   0.6681   0.0023
  -4.250   0.0571   0.00989   0.00352  -0.1016   0.6662   0.0026
  -4.000   0.0842   0.00958   0.00316  -0.1017   0.6645   0.0032
  -3.750   0.1117   0.00937   0.00290  -0.1019   0.6629   0.0039
  -3.250   0.1673   0.00900   0.00249  -0.1023   0.6597   0.0069
  -3.000   0.1953   0.00884   0.00239  -0.1027   0.6579   0.0114
  -2.750   0.2237   0.00879   0.00235  -0.1031   0.6559   0.0144
  -2.500   0.2516   0.00861   0.00214  -0.1034   0.6539   0.0184
  -2.250   0.2798   0.00850   0.00200  -0.1037   0.6521   0.0212
  -2.000   0.3081   0.00842   0.00188  -0.1040   0.6504   0.0237
  -1.750   0.3361   0.00831   0.00178  -0.1043   0.6486   0.0339
  -1.500   0.3634   0.00802   0.00168  -0.1046   0.6468   0.1023
  -1.250   0.3904   0.00764   0.00159  -0.1050   0.6449   0.2037
  -1.000   0.4158   0.00699   0.00150  -0.1053   0.6430   0.3943
  -0.750   0.4407   0.00636   0.00144  -0.1054   0.6410   0.5900
  -0.500   0.4668   0.00607   0.00148  -0.1053   0.6389   0.7005
  -0.250   0.4944   0.00605   0.00154  -0.1055   0.6369   0.7460
   0.000   0.5224   0.00608   0.00158  -0.1057   0.6351   0.7669
   0.250   0.5512   0.00611   0.00160  -0.1061   0.6333   0.7756
   0.500   0.5799   0.00614   0.00163  -0.1065   0.6313   0.7819
   0.750   0.6087   0.00617   0.00165  -0.1070   0.6291   0.7880
   1.000   0.6372   0.00620   0.00168  -0.1074   0.6270   0.7927
   1.250   0.6657   0.00624   0.00171  -0.1078   0.6249   0.7977
   1.500   0.6943   0.00630   0.00174  -0.1082   0.6228   0.8023
   1.750   0.7225   0.00634   0.00179  -0.1086   0.6208   0.8060
   2.000   0.7510   0.00638   0.00185  -0.1091   0.6187   0.8100
   2.250   0.7796   0.00642   0.00190  -0.1095   0.6162   0.8138
   2.500   0.8080   0.00647   0.00194  -0.1099   0.6130   0.8169
   2.750   0.8353   0.00653   0.00200  -0.1101   0.6072   0.8197
   3.000   0.8632   0.00657   0.00206  -0.1105   0.6006   0.8227
   3.250   0.8908   0.00664   0.00212  -0.1108   0.5962   0.8259
   3.500   0.9187   0.00671   0.00220  -0.1111   0.5920   0.8290
   3.750   0.9464   0.00676   0.00229  -0.1115   0.5874   0.8317
   4.000   0.9734   0.00684   0.00239  -0.1117   0.5824   0.8345
   4.250   1.0008   0.00692   0.00249  -0.1119   0.5770   0.8374
   4.500   1.0273   0.00702   0.00260  -0.1120   0.5694   0.8404
   4.750   1.0540   0.00713   0.00273  -0.1122   0.5613   0.8433
   5.000   1.0763   0.00739   0.00291  -0.1115   0.5369   0.8463
   5.250   1.0865   0.00819   0.00341  -0.1087   0.4728   0.8501
   5.500   1.0760   0.00975   0.00445  -0.1024   0.3726   0.8559
   5.750   1.0580   0.01104   0.00541  -0.0946   0.3034   0.8624
   6.000   1.0395   0.01235   0.00653  -0.0872   0.2578   0.8712
   6.250   1.0211   0.01415   0.00813  -0.0809   0.2068   0.8817
   6.500   0.9929   0.01662   0.01027  -0.0738   0.1294   0.8984
   6.750   0.9945   0.01777   0.01137  -0.0707   0.1006   0.9182
   7.000   0.9980   0.02006   0.01342  -0.0701   0.0274   1.0000
   7.250   1.0027   0.02140   0.01467  -0.0679   0.0034   1.0000
   7.500   1.0172   0.02219   0.01549  -0.0668   0.0025   1.0000
   7.750   1.0309   0.02303   0.01638  -0.0657   0.0020   1.0000
   8.000   1.0448   0.02388   0.01727  -0.0646   0.0019   1.0000
   8.250   1.0579   0.02479   0.01822  -0.0635   0.0018   1.0000
   8.500   1.0706   0.02573   0.01920  -0.0624   0.0017   1.0000
   8.750   1.0838   0.02665   0.02016  -0.0613   0.0016   1.0000
   9.000   1.0971   0.02758   0.02110  -0.0604   0.0013   1.0000
   9.250   1.1086   0.02868   0.02226  -0.0592   0.0013   1.0000
   9.500   1.1208   0.02976   0.02337  -0.0582   0.0012   1.0000
   9.750   1.1315   0.03097   0.02465  -0.0571   0.0012   1.0000
  10.000   1.1423   0.03220   0.02593  -0.0560   0.0011   1.0000
  10.250   1.1533   0.03344   0.02722  -0.0551   0.0010   1.0000
  10.500   1.1636   0.03475   0.02858  -0.0541   0.0009   1.0000
  10.750   1.1731   0.03616   0.03004  -0.0530   0.0009   1.0000
  11.000   1.1828   0.03758   0.03150  -0.0521   0.0008   1.0000
  11.250   1.1879   0.03942   0.03340  -0.0509   0.0007   1.0000
  11.500   1.1897   0.04160   0.03568  -0.0494   0.0007   1.0000
  11.750   1.1974   0.04330   0.03744  -0.0485   0.0006   1.0000
  12.000   1.2041   0.04513   0.03934  -0.0476   0.0006   1.0000
  12.250   1.2115   0.04693   0.04121  -0.0467   0.0006   1.0000
  12.500   1.2159   0.04903   0.04339  -0.0458   0.0006   1.0000
  12.750   1.2250   0.05073   0.04515  -0.0452   0.0005   1.0000
  13.000   1.2290   0.05297   0.04749  -0.0444   0.0005   1.0000
  13.250   1.2363   0.05491   0.04951  -0.0438   0.0005   1.0000
  13.500   1.2408   0.05717   0.05187  -0.0431   0.0005   1.0000
  13.750   1.2449   0.05951   0.05430  -0.0424   0.0004   1.0000
  14.000   1.2499   0.06181   0.05669  -0.0418   0.0004   1.0000
  14.250   1.2530   0.06435   0.05934  -0.0411   0.0004   1.0000
  14.500   1.2570   0.06683   0.06193  -0.0406   0.0004   1.0000
  14.750   1.2605   0.06941   0.06464  -0.0401   0.0004   1.0000
  15.000   1.2638   0.07212   0.06747  -0.0396   0.0004   1.0000
  15.250   1.2654   0.07510   0.07061  -0.0392   0.0004   1.0000
  15.500   1.2690   0.07790   0.07351  -0.0393   0.0004   1.0000
  15.750   1.2684   0.08134   0.07712  -0.0390   0.0004   1.0000
  16.000   1.2664   0.08510   0.08105  -0.0391   0.0003   1.0000
  16.250   1.2636   0.08906   0.08518  -0.0394   0.0004   1.0000
  16.500   1.2575   0.09364   0.08995  -0.0399   0.0003   1.0000
  16.750   1.2485   0.09882   0.09535  -0.0408   0.0003   1.0000
  17.000   1.2409   0.10387   0.10057  -0.0420   0.0004   1.0000
  17.250   1.2292   0.10978   0.10667  -0.0436   0.0004   1.0000
  17.500   1.2185   0.11567   0.11273  -0.0456   0.0004   1.0000
  17.750   1.2028   0.12267   0.11993  -0.0482   0.0004   1.0000
  18.000   1.1919   0.12894   0.12635  -0.0509   0.0004   1.0000
  18.250   1.1768   0.13630   0.13389  -0.0544   0.0004   1.0000
  18.500   1.1630   0.14366   0.14140  -0.0581   0.0004   1.0000
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