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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 200,000
Max Cl/Cd: 68.49 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx67k150-il-200000-n5.txt
Download as CSV file: xf-fx67k150-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0534   0.07902   0.07476  -0.0915   0.7517   0.0124
  -9.250  -0.0532   0.07498   0.07075  -0.0928   0.7498   0.0115
  -9.000  -0.0536   0.07092   0.06671  -0.0942   0.7479   0.0109
  -8.750  -0.0552   0.06670   0.06252  -0.0959   0.7462   0.0102
  -8.500  -0.0621   0.06130   0.05715  -0.0983   0.7447   0.0094
  -8.000  -0.1120   0.06042   0.05604  -0.1140   0.7459   0.0081
  -7.750  -0.1242   0.05761   0.05318  -0.1137   0.7437   0.0080
  -7.500  -0.1308   0.05402   0.04946  -0.1139   0.7420   0.0079
  -7.250  -0.1327   0.05076   0.04608  -0.1137   0.7401   0.0077
  -7.000  -0.1314   0.04748   0.04266  -0.1133   0.7374   0.0076
  -6.750  -0.1268   0.04420   0.03914  -0.1127   0.7348   0.0075
  -6.500  -0.1191   0.04096   0.03566  -0.1118   0.7327   0.0073
  -6.250  -0.1081   0.03781   0.03221  -0.1109   0.7308   0.0072
  -6.000  -0.0948   0.03458   0.02863  -0.1097   0.7292   0.0072
  -5.750  -0.0788   0.03151   0.02514  -0.1086   0.7280   0.0072
  -5.500  -0.0607   0.02889   0.02215  -0.1075   0.7257   0.0072
  -5.250  -0.0405   0.02642   0.01927  -0.1064   0.7232   0.0074
  -5.000  -0.0176   0.02436   0.01678  -0.1054   0.7210   0.0079
  -4.750   0.0058   0.02313   0.01534  -0.1052   0.7190   0.0092
  -4.500   0.0309   0.02263   0.01472  -0.1051   0.7173   0.0110
  -4.250   0.0569   0.02138   0.01322  -0.1047   0.7160   0.0122
  -4.000   0.0829   0.02018   0.01182  -0.1042   0.7148   0.0130
  -3.750   0.1078   0.01940   0.01091  -0.1037   0.7127   0.0140
  -3.500   0.1290   0.01820   0.00971  -0.1029   0.7100   0.0167
  -3.250   0.1538   0.01781   0.00926  -0.1027   0.7077   0.0217
  -3.000   0.1778   0.01710   0.00844  -0.1022   0.7057   0.0256
  -2.750   0.2033   0.01666   0.00792  -0.1021   0.7041   0.0333
  -2.500   0.2295   0.01626   0.00744  -0.1020   0.7027   0.0423
  -2.250   0.2559   0.01584   0.00702  -0.1020   0.7016   0.0673
  -2.000   0.2751   0.01475   0.00684  -0.1016   0.6991   0.3178
  -1.750   0.2884   0.01374   0.00710  -0.0994   0.6961   0.6396
  -1.500   0.3050   0.01390   0.00762  -0.0962   0.6937   0.7780
  -1.250   0.3269   0.01409   0.00777  -0.0946   0.6919   0.8154
  -1.000   0.3491   0.01421   0.00783  -0.0931   0.6904   0.8370
  -0.750   0.3757   0.01421   0.00770  -0.0928   0.6891   0.8466
  -0.500   0.4026   0.01420   0.00757  -0.0926   0.6879   0.8550
  -0.250   0.4236   0.01445   0.00783  -0.0917   0.6843   0.8628
   0.000   0.4475   0.01460   0.00792  -0.0913   0.6816   0.8709
   0.250   0.4722   0.01465   0.00792  -0.0909   0.6796   0.8773
   0.500   0.4985   0.01466   0.00787  -0.0908   0.6778   0.8843
   0.750   0.5251   0.01463   0.00778  -0.0907   0.6764   0.8900
   1.000   0.5527   0.01460   0.00769  -0.0908   0.6751   0.8959
   1.250   0.5749   0.01482   0.00792  -0.0902   0.6722   0.9020
   1.500   0.5964   0.01504   0.00817  -0.0895   0.6689   0.9084
   1.750   0.6215   0.01512   0.00824  -0.0893   0.6665   0.9145
   2.000   0.6481   0.01514   0.00825  -0.0893   0.6647   0.9201
   2.250   0.6761   0.01513   0.00823  -0.0897   0.6632   0.9262
   2.500   0.7062   0.01508   0.00816  -0.0903   0.6619   0.9312
   2.750   0.7280   0.01539   0.00852  -0.0899   0.6585   0.9390
   3.000   0.7527   0.01567   0.00886  -0.0900   0.6550   0.9461
   3.250   0.7819   0.01575   0.00899  -0.0908   0.6527   0.9534
   3.500   0.8153   0.01576   0.00902  -0.0923   0.6509   0.9595
   3.750   0.8496   0.01573   0.00901  -0.0940   0.6494   0.9662
   4.000   0.8860   0.01567   0.00897  -0.0961   0.6481   0.9724
   4.500   0.9359   0.01645   0.00997  -0.0972   0.6396   1.0000
   4.750   0.9634   0.01646   0.01001  -0.0975   0.6373   1.0000
   5.000   0.9936   0.01639   0.00997  -0.0983   0.6356   1.0000
   5.250   1.0097   0.01689   0.01061  -0.0971   0.6308   1.0000
   5.500   1.0320   0.01703   0.01083  -0.0966   0.6260   1.0000
   5.750   1.0674   0.01651   0.01034  -0.0978   0.6222   1.0000
   6.000   1.0798   0.01693   0.01086  -0.0959   0.6143   1.0000
   6.250   1.1123   0.01652   0.01049  -0.0966   0.6090   1.0000
   6.500   1.1236   0.01701   0.01115  -0.0945   0.6017   1.0000
   6.750   1.1470   0.01677   0.01096  -0.0938   0.5917   1.0000
   7.000   1.1520   0.01682   0.01101  -0.0900   0.5713   1.0000
   7.250   1.1624   0.01714   0.01137  -0.0875   0.5567   1.0000
   7.500   1.1675   0.01767   0.01184  -0.0844   0.5295   1.0000
   7.750   1.1618   0.01861   0.01229  -0.0797   0.4542   1.0000
   8.000   1.1446   0.02068   0.01391  -0.0745   0.3930   1.0000
   8.250   1.1311   0.02286   0.01581  -0.0702   0.3467   1.0000
   8.500   1.1035   0.02607   0.01856  -0.0649   0.2794   1.0000
   8.750   1.0865   0.02890   0.02103  -0.0611   0.2222   1.0000
   9.000   1.0670   0.03207   0.02374  -0.0573   0.1524   1.0000
   9.250   1.0396   0.03612   0.02709  -0.0533   0.0545   1.0000
   9.500   1.0388   0.03837   0.02918  -0.0515   0.0244   1.0000
   9.750   1.0426   0.04032   0.03106  -0.0502   0.0088   1.0000
  10.000   1.0509   0.04195   0.03276  -0.0491   0.0069   1.0000
  10.250   1.0601   0.04354   0.03447  -0.0481   0.0063   1.0000
  10.500   1.0693   0.04516   0.03629  -0.0472   0.0059   1.0000
  10.750   1.0780   0.04687   0.03813  -0.0464   0.0057   1.0000
  11.000   1.0854   0.04872   0.04013  -0.0455   0.0055   1.0000
  11.250   1.0922   0.05068   0.04223  -0.0446   0.0053   1.0000
  11.500   1.0968   0.05291   0.04459  -0.0437   0.0051   1.0000
  11.750   1.1021   0.05512   0.04693  -0.0430   0.0050   1.0000
  12.000   1.1056   0.05753   0.04948  -0.0422   0.0049   1.0000
  12.250   1.1091   0.06001   0.05207  -0.0414   0.0048   1.0000
  12.500   1.1132   0.06245   0.05463  -0.0408   0.0048   1.0000
  12.750   1.1171   0.06494   0.05723  -0.0401   0.0046   1.0000
  13.000   1.1227   0.06726   0.05965  -0.0395   0.0045   1.0000
  13.250   1.1288   0.06953   0.06201  -0.0391   0.0042   1.0000
  13.500   1.1322   0.07212   0.06466  -0.0385   0.0037   1.0000
  13.750   1.1392   0.07437   0.06702  -0.0378   0.0034   1.0000
  14.000   1.1482   0.07646   0.06932  -0.0375   0.0032   1.0000
  14.250   1.1571   0.07862   0.07165  -0.0369   0.0030   1.0000
  14.500   1.1655   0.08093   0.07414  -0.0364   0.0029   1.0000
  14.750   1.1727   0.08350   0.07690  -0.0359   0.0029   1.0000
  15.000   1.1779   0.08641   0.08003  -0.0356   0.0028   1.0000
  15.250   1.1804   0.08977   0.08363  -0.0355   0.0028   1.0000
  15.500   1.1810   0.09338   0.08748  -0.0357   0.0028   1.0000
  15.750   1.1782   0.09760   0.09195  -0.0361   0.0028   1.0000
  16.000   1.1729   0.10226   0.09687  -0.0368   0.0027   1.0000
  16.250   1.1658   0.10723   0.10208  -0.0379   0.0028   1.0000
  16.500   1.1568   0.11265   0.10775  -0.0395   0.0028   1.0000
  16.750   1.1456   0.11862   0.11396  -0.0415   0.0027   1.0000
  17.000   1.1349   0.12463   0.12019  -0.0439   0.0028   1.0000
  17.250   1.1222   0.13127   0.12705  -0.0468   0.0028   1.0000
  17.500   1.1096   0.13813   0.13411  -0.0502   0.0028   1.0000
  17.750   1.0954   0.14571   0.14189  -0.0543   0.0028   1.0000
  18.000   1.0830   0.15321   0.14956  -0.0587   0.0029   1.0000
  18.250   1.0692   0.16153   0.15804  -0.0637   0.0029   1.0000
  18.500   1.0561   0.17026   0.16692  -0.0692   0.0029   1.0000
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