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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 1,000,000
Max Cl/Cd: 157.21 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx67k150-il-1000000.txt
Download as CSV file: xf-fx67k150-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0948   0.08410   0.08126  -0.1002   0.7311   0.0065
  -9.500  -0.0933   0.08036   0.07753  -0.1019   0.7296   0.0069
  -9.250  -0.0923   0.07624   0.07342  -0.1040   0.7280   0.0074
  -9.000  -0.0920   0.07263   0.06980  -0.1058   0.7261   0.0073
  -8.750  -0.0887   0.06875   0.06597  -0.1081   0.7247   0.0077
  -8.500  -0.0929   0.06441   0.06166  -0.1108   0.7228   0.0076
  -5.500  -0.0646   0.01888   0.01390  -0.1054   0.7009   0.0066
  -5.250  -0.0411   0.01695   0.01165  -0.1046   0.6991   0.0070
  -5.000  -0.0164   0.01534   0.00983  -0.1041   0.6977   0.0072
  -4.750   0.0093   0.01416   0.00850  -0.1039   0.6960   0.0073
  -4.500   0.0356   0.01325   0.00747  -0.1037   0.6941   0.0075
  -4.250   0.0630   0.01287   0.00701  -0.1038   0.6923   0.0080
  -4.000   0.0877   0.01166   0.00569  -0.1033   0.6907   0.0081
  -3.750   0.1124   0.01074   0.00467  -0.1029   0.6891   0.0082
  -3.500   0.1371   0.00993   0.00373  -0.1025   0.6874   0.0087
  -3.250   0.1642   0.00960   0.00334  -0.1026   0.6856   0.0103
  -3.000   0.1923   0.00944   0.00318  -0.1028   0.6840   0.0128
  -2.750   0.2195   0.00909   0.00282  -0.1029   0.6821   0.0200
  -2.500   0.2476   0.00894   0.00264  -0.1032   0.6803   0.0230
  -2.250   0.2756   0.00874   0.00243  -0.1035   0.6785   0.0300
  -2.000   0.3037   0.00856   0.00225  -0.1038   0.6768   0.0442
  -1.750   0.3272   0.00758   0.00203  -0.1039   0.6751   0.2975
  -1.500   0.3512   0.00681   0.00193  -0.1040   0.6731   0.5240
  -1.250   0.3768   0.00639   0.00192  -0.1039   0.6714   0.6573
  -1.000   0.4035   0.00625   0.00199  -0.1038   0.6697   0.7353
  -0.750   0.4313   0.00627   0.00206  -0.1039   0.6678   0.7709
  -0.500   0.4595   0.00631   0.00210  -0.1041   0.6658   0.7902
  -0.250   0.4875   0.00637   0.00216  -0.1042   0.6639   0.8052
   0.000   0.5160   0.00642   0.00218  -0.1045   0.6622   0.8134
   0.250   0.5446   0.00648   0.00220  -0.1049   0.6602   0.8190
   0.500   0.5730   0.00652   0.00224  -0.1053   0.6583   0.8239
   0.750   0.6017   0.00655   0.00227  -0.1057   0.6565   0.8289
   1.000   0.6301   0.00657   0.00229  -0.1060   0.6545   0.8331
   1.250   0.6586   0.00659   0.00232  -0.1064   0.6524   0.8373
   1.500   0.6872   0.00662   0.00234  -0.1068   0.6504   0.8416
   1.750   0.7158   0.00666   0.00236  -0.1073   0.6485   0.8453
   2.000   0.7442   0.00673   0.00241  -0.1077   0.6462   0.8488
   2.250   0.7723   0.00675   0.00247  -0.1080   0.6442   0.8525
   2.500   0.8007   0.00678   0.00252  -0.1085   0.6419   0.8560
   2.750   0.8291   0.00680   0.00256  -0.1089   0.6394   0.8591
   3.000   0.8571   0.00681   0.00259  -0.1092   0.6370   0.8621
   3.250   0.8852   0.00685   0.00262  -0.1096   0.6340   0.8653
   3.500   0.9129   0.00687   0.00267  -0.1099   0.6297   0.8686
   3.750   0.9408   0.00687   0.00271  -0.1102   0.6249   0.8717
   4.000   0.9683   0.00689   0.00275  -0.1105   0.6217   0.8748
   4.250   0.9958   0.00695   0.00282  -0.1107   0.6183   0.8780
   4.500   1.0232   0.00697   0.00290  -0.1110   0.6142   0.8814
   4.750   1.0507   0.00701   0.00298  -0.1113   0.6097   0.8847
   5.000   1.0773   0.00706   0.00305  -0.1114   0.6044   0.8880
   5.250   1.1027   0.00708   0.00310  -0.1112   0.5936   0.8917
   5.500   1.1272   0.00717   0.00318  -0.1109   0.5783   0.8956
   5.750   1.1497   0.00736   0.00332  -0.1103   0.5540   0.8999
   6.000   1.1670   0.00773   0.00359  -0.1086   0.5176   0.9049
   6.250   1.1646   0.00887   0.00434  -0.1036   0.4366   0.9138
   6.500   1.1521   0.01004   0.00522  -0.0966   0.3706   0.9289
   6.750   1.1321   0.01163   0.00655  -0.0894   0.3019   1.0000
   7.000   1.1073   0.01400   0.00858  -0.0829   0.2380   1.0000
   7.250   1.0881   0.01639   0.01063  -0.0776   0.1738   1.0000
   7.500   1.0749   0.01860   0.01253  -0.0731   0.1176   1.0000
   7.750   1.0506   0.02156   0.01505  -0.0676   0.0346   1.0000
   8.000   1.0503   0.02324   0.01660  -0.0650   0.0055   1.0000
   8.250   1.0639   0.02411   0.01750  -0.0639   0.0048   1.0000
   8.500   1.0752   0.02515   0.01859  -0.0625   0.0040   1.0000
   8.750   1.0875   0.02613   0.01962  -0.0613   0.0038   1.0000
   9.000   1.0990   0.02718   0.02073  -0.0601   0.0037   1.0000
   9.250   1.1098   0.02832   0.02194  -0.0588   0.0036   1.0000
   9.500   1.1204   0.02950   0.02318  -0.0576   0.0036   1.0000
   9.750   1.1285   0.03091   0.02466  -0.0562   0.0035   1.0000
  10.000   1.1379   0.03226   0.02607  -0.0549   0.0035   1.0000
  10.250   1.1381   0.03436   0.02829  -0.0530   0.0032   1.0000
  10.500   1.1446   0.03602   0.03002  -0.0516   0.0033   1.0000
  10.750   1.1530   0.03756   0.03161  -0.0506   0.0031   1.0000
  11.000   1.1568   0.03952   0.03366  -0.0491   0.0031   1.0000
  11.250   1.1599   0.04159   0.03581  -0.0477   0.0031   1.0000
  11.500   1.1692   0.04314   0.03741  -0.0469   0.0030   1.0000
  11.750   1.1733   0.04520   0.03955  -0.0456   0.0030   1.0000
  12.000   1.1807   0.04698   0.04139  -0.0447   0.0030   1.0000
  12.250   1.1849   0.04905   0.04357  -0.0435   0.0030   1.0000
  12.500   1.1958   0.05059   0.04517  -0.0430   0.0028   1.0000
  12.750   1.2046   0.05232   0.04696  -0.0423   0.0026   1.0000
  13.000   1.2124   0.05416   0.04888  -0.0415   0.0025   1.0000
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