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FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 73-K-170/22 (fx73k170-il)
Reynolds number: 50,000
Max Cl/Cd: 5.2 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73k170-il-50000.txt
Download as CSV file: xf-fx73k170-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-K-170/22                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.4583   0.12578   0.12082  -0.0053   1.0000   0.3398
  -6.750  -0.4742   0.12420   0.11931  -0.0032   1.0000   0.3520
  -6.500  -0.4983   0.12344   0.11864  -0.0005   1.0000   0.3657
  -6.250  -0.4733   0.11911   0.11428   0.0003   1.0000   0.3720
  -6.000  -0.4155   0.11728   0.11300  -0.0008   1.0000   0.3661
  -5.750  -0.4038   0.11389   0.10960   0.0000   1.0000   0.3697
  -5.500  -0.4109   0.11097   0.10671   0.0011   1.0000   0.3714
  -5.250  -0.6427   0.07131   0.06492  -0.0432   1.0000   0.1297
  -5.000  -0.6292   0.06725   0.06088  -0.0429   1.0000   0.1259
  -4.750  -0.6079   0.06187   0.05429  -0.0459   1.0000   0.1146
  -4.500  -0.5903   0.05843   0.05066  -0.0459   1.0000   0.1128
  -4.250  -0.5706   0.05529   0.04714  -0.0461   1.0000   0.1105
  -4.000  -0.5492   0.05253   0.04389  -0.0461   1.0000   0.1085
  -3.750  -0.5276   0.05034   0.04126  -0.0459   1.0000   0.1074
  -3.500  -0.5059   0.04854   0.03906  -0.0454   1.0000   0.1084
  -3.250  -0.4844   0.04721   0.03735  -0.0447   1.0000   0.1118
  -3.000  -0.4632   0.04581   0.03571  -0.0439   1.0000   0.1178
  -2.750  -0.4431   0.04489   0.03476  -0.0428   1.0000   0.1227
  -2.500  -0.4230   0.04409   0.03387  -0.0413   1.0000   0.1332
  -2.250  -0.4037   0.04359   0.03333  -0.0398   1.0000   0.1459
  -2.000  -0.3849   0.04284   0.03283  -0.0384   1.0000   0.1685
  -1.750  -0.3639   0.04169   0.03216  -0.0379   1.0000   0.2267
  -1.500  -0.3761   0.04172   0.03491  -0.0255   1.0000   0.6707
  -1.250  -0.3834   0.04279   0.03598  -0.0154   1.0000   0.7358
  -1.000  -0.3876   0.04322   0.03632  -0.0069   1.0000   0.7840
  -0.750  -0.3898   0.04326   0.03626   0.0005   1.0000   0.8261
  -0.500  -0.3926   0.04298   0.03590   0.0080   1.0000   0.8728
  -0.250  -0.2342   0.04873   0.04100  -0.0134   1.0000   0.9897
   0.000  -0.2112   0.04933   0.04134  -0.0159   1.0000   1.0000
   0.250  -0.2118   0.04854   0.04044  -0.0138   1.0000   1.0000
   0.500  -0.2114   0.04779   0.03958  -0.0118   1.0000   1.0000
   0.750  -0.2085   0.04719   0.03884  -0.0102   1.0000   1.0000
   1.000  -0.2020   0.04687   0.03838  -0.0093   1.0000   1.0000
   1.250  -0.1788   0.04780   0.03909  -0.0114   0.9964   1.0000
   1.500  -0.1467   0.04944   0.04048  -0.0153   0.9887   1.0000
   1.750  -0.1155   0.05095   0.04178  -0.0188   0.9796   1.0000
   2.000  -0.0863   0.05236   0.04298  -0.0218   0.9703   1.0000
   2.250  -0.0536   0.05437   0.04479  -0.0255   0.9629   1.0000
   2.500  -0.0210   0.05614   0.04638  -0.0290   0.9525   1.0000
   2.750   0.0030   0.05723   0.04735  -0.0310   0.9423   1.0000
   3.000   0.0432   0.06035   0.05028  -0.0358   0.9358   1.0000
   3.250   0.0627   0.06084   0.05069  -0.0368   0.9240   1.0000
   3.500   0.0869   0.06238   0.05213  -0.0388   0.9155   1.0000
   3.750   0.1221   0.06489   0.05449  -0.0425   0.9065   1.0000
   4.000   0.1396   0.06574   0.05528  -0.0432   0.8959   1.0000
   4.250   0.1792   0.06922   0.05863  -0.0477   0.8900   1.0000
   4.500   0.1926   0.06955   0.05893  -0.0477   0.8783   1.0000
   4.750   0.2130   0.07120   0.06053  -0.0490   0.8706   1.0000
   5.000   0.2445   0.07367   0.06293  -0.0520   0.8615   1.0000
   5.250   0.2577   0.07466   0.06390  -0.0520   0.8518   1.0000
   5.500   0.2948   0.07812   0.06731  -0.0559   0.8451   1.0000
   5.750   0.3024   0.07852   0.06771  -0.0551   0.8345   1.0000
   6.000   0.3334   0.08174   0.07088  -0.0581   0.8288   1.0000
   6.250   0.3457   0.08262   0.07177  -0.0580   0.8177   1.0000
   6.500   0.3626   0.08464   0.07379  -0.0589   0.8107   1.0000
   6.750   0.3882   0.08698   0.07615  -0.0608   0.8010   1.0000
   7.000   0.3973   0.08837   0.07755  -0.0605   0.7928   1.0000
   7.250   0.4293   0.09160   0.08079  -0.0634   0.7846   1.0000
   7.500   0.4331   0.09249   0.08172  -0.0624   0.7750   1.0000
   7.750   0.4712   0.09677   0.08604  -0.0661   0.7683   1.0000
   8.000   0.4694   0.09696   0.08628  -0.0645   0.7573   1.0000
   8.250   0.4886   0.09975   0.08911  -0.0658   0.7508   1.0000
   8.500   0.5078   0.10190   0.09132  -0.0668   0.7399   1.0000
   8.750   0.5137   0.10353   0.09301  -0.0665   0.7308   1.0000
   9.000   0.5475   0.10756   0.09712  -0.0694   0.7227   1.0000
   9.250   0.5499   0.10848   0.09812  -0.0686   0.7112   1.0000
   9.500   0.5585   0.11059   0.10030  -0.0688   0.7022   1.0000
   9.750   0.5892   0.11440   0.10423  -0.0712   0.6931   1.0000
  10.000   0.5961   0.11587   0.10579  -0.0711   0.6809   1.0000
  10.250   0.6011   0.11784   0.10784  -0.0710   0.6707   1.0000
  10.500   0.6176   0.12074   0.11084  -0.0721   0.6612   1.0000
  10.750   0.6467   0.12438   0.11462  -0.0741   0.6494   1.0000
  11.000   0.6512   0.12595   0.11629  -0.0740   0.6366   1.0000
  11.250   0.6559   0.12806   0.11849  -0.0741   0.6248   1.0000
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