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FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 60-160 AIRFOIL (fx60160-il)
Reynolds number: 50,000
Max Cl/Cd: 23.41 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60160-il-50000.txt
Download as CSV file: xf-fx60160-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-160 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2906   0.12012   0.11425  -0.0186   1.0000   0.3632
  -9.000  -0.3103   0.11943   0.11366  -0.0164   1.0000   0.3733
  -8.750  -0.3486   0.11357   0.10709  -0.0199   1.0000   0.4032
  -8.250  -0.3549   0.10964   0.10330  -0.0151   1.0000   0.4182
  -8.000  -0.3651   0.10777   0.10152  -0.0127   1.0000   0.4215
  -7.750  -0.3692   0.10552   0.09932  -0.0108   1.0000   0.4231
  -7.500  -0.3317   0.10676   0.10124  -0.0068   1.0000   0.4091
  -7.250  -0.3400   0.10436   0.09889  -0.0055   1.0000   0.4098
  -7.000  -0.6379   0.07711   0.07148  -0.0299   1.0000   0.2076
  -6.750  -0.6770   0.06635   0.06004  -0.0369   1.0000   0.1799
  -6.500  -0.6771   0.06007   0.05303  -0.0393   1.0000   0.1647
  -6.250  -0.6658   0.05602   0.04873  -0.0394   1.0000   0.1589
  -6.000  -0.6528   0.05192   0.04391  -0.0404   1.0000   0.1539
  -5.750  -0.6358   0.04908   0.04038  -0.0408   1.0000   0.1520
  -5.500  -0.6168   0.04687   0.03761  -0.0407   1.0000   0.1510
  -5.250  -0.5967   0.04483   0.03515  -0.0404   1.0000   0.1503
  -5.000  -0.5764   0.04291   0.03287  -0.0399   1.0000   0.1503
  -4.750  -0.5568   0.04085   0.03071  -0.0394   1.0000   0.1529
  -4.500  -0.5372   0.03941   0.02919  -0.0388   1.0000   0.1567
  -4.250  -0.5165   0.03825   0.02783  -0.0380   1.0000   0.1594
  -4.000  -0.4957   0.03726   0.02664  -0.0371   1.0000   0.1622
  -3.750  -0.4750   0.03659   0.02568  -0.0361   1.0000   0.1666
  -3.500  -0.4569   0.03564   0.02496  -0.0346   1.0000   0.1738
  -3.250  -0.4380   0.03516   0.02439  -0.0331   1.0000   0.1812
  -3.000  -0.4206   0.03456   0.02393  -0.0315   1.0000   0.1890
  -2.750  -0.4022   0.03399   0.02343  -0.0305   1.0000   0.2030
  -2.500  -0.3828   0.03327   0.02295  -0.0301   1.0000   0.2262
  -2.250  -0.3591   0.03158   0.02269  -0.0312   1.0000   0.3643
  -2.000  -0.3645   0.03313   0.02543  -0.0214   1.0000   0.6426
  -1.750  -0.3709   0.03491   0.02724  -0.0115   1.0000   0.7109
  -1.500  -0.3724   0.03578   0.02801  -0.0039   1.0000   0.7539
  -1.250  -0.3743   0.03612   0.02829   0.0034   1.0000   0.7886
  -1.000  -0.3740   0.03616   0.02824   0.0096   1.0000   0.8213
  -0.750  -0.3732   0.03599   0.02799   0.0154   1.0000   0.8541
  -0.500  -0.3726   0.03565   0.02761   0.0215   1.0000   0.8930
  -0.250  -0.1672   0.04197   0.03330  -0.0085   0.9870   0.9823
   0.000  -0.0764   0.04388   0.03486  -0.0232   0.9641   0.9927
   0.250  -0.0264   0.04487   0.03565  -0.0303   0.9515   1.0000
   0.500  -0.0266   0.04478   0.03552  -0.0283   0.9477   1.0000
   0.750  -0.0230   0.04487   0.03555  -0.0270   0.9437   1.0000
   1.000  -0.0171   0.04519   0.03579  -0.0261   0.9405   1.0000
   1.250  -0.1541   0.03990   0.03080  -0.0001   1.0000   1.0000
   1.500  -0.1479   0.03983   0.03064   0.0007   1.0000   1.0000
   1.750  -0.1358   0.04012   0.03083   0.0005   1.0000   1.0000
   2.000  -0.1200   0.04069   0.03129  -0.0004   1.0000   1.0000
   2.250  -0.1019   0.04147   0.03197  -0.0017   1.0000   1.0000
   2.500  -0.0645   0.04370   0.03406  -0.0067   0.9934   1.0000
   2.750  -0.0312   0.04553   0.03579  -0.0108   0.9848   1.0000
   3.000  -0.0023   0.04720   0.03737  -0.0141   0.9772   1.0000
   3.250   0.0364   0.04986   0.03993  -0.0190   0.9687   1.0000
   3.500   0.0624   0.05118   0.04119  -0.0217   0.9582   1.0000
   3.750   0.0882   0.05290   0.04286  -0.0242   0.9509   1.0000
   4.000   0.1257   0.05556   0.04546  -0.0288   0.9405   1.0000
   4.250   0.1431   0.05648   0.04636  -0.0298   0.9307   1.0000
   4.500   0.1757   0.05910   0.04894  -0.0335   0.9233   1.0000
   4.750   0.2005   0.06064   0.05047  -0.0356   0.9115   1.0000
   5.000   0.2195   0.06207   0.05190  -0.0369   0.9014   1.0000
   5.250   0.2526   0.06488   0.05469  -0.0405   0.8931   1.0000
   5.500   0.2742   0.06637   0.05620  -0.0420   0.8811   1.0000
   5.750   0.2910   0.06786   0.05771  -0.0429   0.8706   1.0000
   6.000   0.3206   0.07057   0.06044  -0.0458   0.8620   1.0000
   6.250   0.3459   0.07260   0.06250  -0.0479   0.8495   1.0000
   6.500   0.3593   0.07396   0.06390  -0.0482   0.8378   1.0000
   6.750   0.3807   0.07625   0.06623  -0.0498   0.8285   1.0000
   7.000   0.4167   0.07952   0.06956  -0.0533   0.8168   1.0000
   7.250   0.4247   0.08052   0.07061  -0.0528   0.8042   1.0000
   7.500   0.4392   0.08244   0.07260  -0.0534   0.7930   1.0000
   7.750   0.4682   0.08558   0.07582  -0.0560   0.7835   1.0000
   8.000   0.4896   0.08777   0.07810  -0.0573   0.7700   1.0000
   8.250   0.4973   0.08933   0.07973  -0.0570   0.7576   1.0000
   8.500   0.5125   0.09170   0.08218  -0.0578   0.7468   1.0000
   8.750   0.5444   0.09523   0.08585  -0.0605   0.7361   1.0000
   9.000   0.5564   0.09706   0.08778  -0.0608   0.7225   1.0000
   9.250   0.5621   0.09898   0.08979  -0.0606   0.7107   1.0000
   9.500   0.5784   0.10183   0.09276  -0.0616   0.7007   1.0000
   9.750   0.6028   0.10496   0.09605  -0.0632   0.6874   1.0000
  10.000   0.6130   0.10683   0.09804  -0.0632   0.6691   1.0000
  10.250   1.0198   0.05573   0.04852  -0.0466   0.4561   1.0000
  10.500   1.0664   0.04556   0.03823  -0.0377   0.3410   1.0000
  10.750   1.0595   0.04725   0.03885  -0.0336   0.2573   1.0000
  11.000   1.0570   0.04985   0.04081  -0.0313   0.2245   1.0000
  11.250   1.0652   0.05196   0.04262  -0.0298   0.2022   1.0000
  11.500   1.0873   0.05324   0.04368  -0.0286   0.1855   1.0000
  11.750   1.1366   0.05346   0.04384  -0.0283   0.1714   1.0000
  12.000   1.1955   0.05423   0.04460  -0.0293   0.1587   1.0000
  12.250   1.2697   0.05628   0.04671  -0.0325   0.1490   1.0000
  12.500   1.2936   0.05912   0.04990  -0.0323   0.1438   1.0000
  12.750   1.3414   0.06306   0.05392  -0.0347   0.1368   1.0000
  13.000   1.3326   0.06623   0.05751  -0.0318   0.1353   1.0000
  13.250   1.3200   0.06968   0.06134  -0.0292   0.1338   1.0000
  13.500   1.3038   0.07341   0.06540  -0.0268   0.1322   1.0000
  13.750   1.2852   0.07750   0.06979  -0.0250   0.1310   1.0000
  14.000   1.2610   0.08220   0.07479  -0.0236   0.1308   1.0000
  14.250   1.2291   0.08777   0.08065  -0.0230   0.1315   1.0000
  14.500   1.1931   0.09435   0.08750  -0.0235   0.1331   1.0000
  14.750   1.1573   0.10185   0.09520  -0.0251   0.1349   1.0000
  15.000   1.1247   0.11002   0.10352  -0.0278   0.1364   1.0000
  15.250   1.0976   0.11860   0.11219  -0.0310   0.1375   1.0000
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