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FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 74-CL6-140 (fx74cl6140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 157.87 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74cl6140-il-1000000.txt
Download as CSV file: xf-fx74cl6140-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-CL6-140                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0630   0.09354   0.08984  -0.0779   0.4988   0.0096
 -10.000   0.0683   0.09042   0.08671  -0.0790   0.4972   0.0097
  -9.750   0.0702   0.08686   0.08314  -0.0806   0.4957   0.0097
  -9.500   0.0747   0.08358   0.07986  -0.0817   0.4943   0.0098
  -9.250   0.0827   0.08021   0.07651  -0.0820   0.4936   0.0100
  -9.000   0.0900   0.07739   0.07370  -0.0828   0.4928   0.0100
  -8.750   0.0971   0.07462   0.07093  -0.0835   0.4918   0.0101
  -8.500   0.1047   0.07206   0.06839  -0.0842   0.4905   0.0103
  -8.250   0.1120   0.06947   0.06581  -0.0850   0.4894   0.0107
  -8.000   0.1175   0.06653   0.06287  -0.0858   0.4883   0.0108
  -7.750   0.1231   0.06365   0.06000  -0.0867   0.4871   0.0110
  -7.500   0.1283   0.06077   0.05714  -0.0875   0.4859   0.0114
  -7.250   0.1327   0.05779   0.05416  -0.0884   0.4847   0.0116
  -7.000   0.1347   0.05445   0.05083  -0.0896   0.4837   0.0121
  -6.750   0.1313   0.05048   0.04689  -0.0917   0.4829   0.0123
  -6.500   0.1305   0.04742   0.04385  -0.0924   0.4818   0.0123
  -6.250   0.1306   0.04449   0.04094  -0.0936   0.4805   0.0124
  -6.000   0.1360   0.04073   0.03718  -0.0971   0.4792   0.0124
  -5.750   0.1417   0.03684   0.03329  -0.1011   0.4776   0.0126
  -5.500   0.1551   0.03327   0.02970  -0.1062   0.4770   0.0127
  -5.250   0.1713   0.03030   0.02671  -0.1097   0.4763   0.0128
  -5.000   0.1901   0.02695   0.02331  -0.1138   0.4755   0.0131
  -4.750   0.2119   0.02344   0.01973  -0.1180   0.4745   0.0134
  -4.500   0.2370   0.01966   0.01581  -0.1224   0.4735   0.0139
  -4.250   0.2726   0.01187   0.00752  -0.1305   0.4727   0.0156
  -4.000   0.2990   0.01097   0.00655  -0.1317   0.4713   0.0160
  -3.500   0.3824   0.01550   0.00943  -0.1443   0.4702   0.0154
  -3.250   0.4121   0.01434   0.00812  -0.1448   0.4688   0.0149
  -3.000   0.4420   0.01375   0.00730  -0.1451   0.4675   0.0152
  -2.750   0.4716   0.01267   0.00607  -0.1455   0.4661   0.0151
  -2.500   0.5011   0.01183   0.00510  -0.1458   0.4646   0.0154
  -2.250   0.5301   0.01135   0.00458  -0.1461   0.4627   0.0160
  -2.000   0.5591   0.01114   0.00432  -0.1463   0.4609   0.0165
  -1.750   0.5887   0.01086   0.00402  -0.1466   0.4601   0.0169
  -1.500   0.6182   0.01062   0.00377  -0.1469   0.4592   0.0174
  -1.250   0.6477   0.01045   0.00358  -0.1472   0.4581   0.0180
  -1.000   0.6774   0.01023   0.00334  -0.1475   0.4570   0.0189
  -0.750   0.7069   0.01009   0.00320  -0.1478   0.4557   0.0199
  -0.500   0.7363   0.01000   0.00308  -0.1481   0.4544   0.0214
  -0.250   0.7657   0.00990   0.00297  -0.1484   0.4530   0.0240
   0.000   0.7952   0.00978   0.00288  -0.1487   0.4517   0.0375
   0.250   0.8250   0.00956   0.00289  -0.1492   0.4504   0.1219
   0.500   0.8550   0.00930   0.00294  -0.1500   0.4490   0.2644
   0.750   0.8855   0.00867   0.00316  -0.1512   0.4472   0.6495
   1.000   0.9136   0.00885   0.00334  -0.1512   0.4451   0.6903
   1.250   0.9420   0.00889   0.00342  -0.1512   0.4443   0.7141
   1.500   0.9701   0.00897   0.00351  -0.1511   0.4435   0.7352
   1.750   0.9984   0.00901   0.00357  -0.1512   0.4424   0.7452
   2.000   1.0268   0.00908   0.00363  -0.1512   0.4411   0.7536
   2.250   1.0547   0.00913   0.00369  -0.1512   0.4397   0.7646
   2.500   1.0830   0.00920   0.00376  -0.1513   0.4384   0.7732
   2.750   1.1111   0.00924   0.00381  -0.1514   0.4371   0.7779
   3.000   1.1394   0.00930   0.00386  -0.1515   0.4357   0.7804
   3.250   1.1676   0.00938   0.00392  -0.1517   0.4342   0.7827
   3.500   1.1957   0.00949   0.00400  -0.1518   0.4326   0.7849
   3.750   1.2236   0.00966   0.00414  -0.1519   0.4306   0.7872
   4.000   1.2516   0.00979   0.00427  -0.1521   0.4291   0.7896
   4.250   1.2796   0.00981   0.00433  -0.1522   0.4281   0.7926
   4.500   1.3076   0.00986   0.00442  -0.1524   0.4268   0.7957
   4.750   1.3356   0.00993   0.00451  -0.1525   0.4255   0.7988
   5.000   1.3635   0.01000   0.00460  -0.1527   0.4240   0.8020
   5.250   1.3913   0.01007   0.00468  -0.1529   0.4224   0.8054
   5.500   1.4188   0.01013   0.00478  -0.1530   0.4208   0.8094
   5.750   1.4463   0.01021   0.00488  -0.1531   0.4192   0.8140
   6.000   1.4735   0.01033   0.00501  -0.1531   0.4175   0.8195
   6.250   1.5003   0.01051   0.00521  -0.1532   0.4153   0.8262
   6.500   1.5273   0.01061   0.00537  -0.1532   0.4137   0.8348
   6.750   1.5543   0.01064   0.00548  -0.1533   0.4123   0.8471
   7.000   1.5803   0.01065   0.00562  -0.1531   0.4107   0.8735
   7.250   1.6051   0.01058   0.00571  -0.1527   0.4090   1.0000
   7.500   1.6324   0.01068   0.00584  -0.1528   0.4071   1.0000
   7.750   1.6594   0.01079   0.00598  -0.1530   0.4051   1.0000
   8.000   1.6860   0.01094   0.00613  -0.1530   0.4030   1.0000
   8.250   1.7119   0.01117   0.00635  -0.1530   0.4004   1.0000
   8.500   1.7384   0.01130   0.00654  -0.1530   0.3985   1.0000
   8.750   1.7650   0.01140   0.00670  -0.1531   0.3964   1.0000
   9.000   1.7913   0.01149   0.00685  -0.1531   0.3935   1.0000
   9.250   1.8169   0.01158   0.00695  -0.1530   0.3891   1.0000
   9.500   1.8415   0.01176   0.00713  -0.1528   0.3840   1.0000
   9.750   1.8676   0.01183   0.00727  -0.1528   0.3789   1.0000
  10.000   1.8915   0.01203   0.00746  -0.1525   0.3725   1.0000
  10.250   1.9163   0.01220   0.00767  -0.1523   0.3661   1.0000
  10.500   1.9390   0.01247   0.00794  -0.1518   0.3582   1.0000
  10.750   1.9625   0.01271   0.00822  -0.1515   0.3506   1.0000
  11.000   1.9835   0.01308   0.00857  -0.1507   0.3432   1.0000
  11.250   2.0057   0.01337   0.00892  -0.1502   0.3353   1.0000
  11.500   2.0248   0.01382   0.00936  -0.1492   0.3262   1.0000
  11.750   2.0422   0.01433   0.00986  -0.1479   0.3158   1.0000
  12.000   2.0582   0.01488   0.01041  -0.1464   0.3044   1.0000
  12.250   2.0685   0.01559   0.01110  -0.1440   0.2909   1.0000
  12.500   2.0708   0.01647   0.01194  -0.1402   0.2759   1.0000
  12.750   2.0658   0.01770   0.01310  -0.1356   0.2592   1.0000
  13.000   2.0577   0.01918   0.01454  -0.1310   0.2431   1.0000
  13.250   2.0417   0.02133   0.01664  -0.1262   0.2255   1.0000
  13.500   2.0207   0.02428   0.01957  -0.1221   0.2098   1.0000
  13.750   1.9942   0.02842   0.02373  -0.1189   0.1955   1.0000
  14.000   1.9695   0.03324   0.02859  -0.1172   0.1852   1.0000
  14.250   1.9398   0.03909   0.03449  -0.1161   0.1758   1.0000
  14.500   1.9123   0.04493   0.04039  -0.1153   0.1674   1.0000
  14.750   1.8832   0.05100   0.04653  -0.1146   0.1603   1.0000
  15.000   1.8532   0.05732   0.05289  -0.1142   0.1520   1.0000
  15.250   1.8255   0.06365   0.05924  -0.1141   0.1419   1.0000
  15.500   1.8020   0.06972   0.06533  -0.1143   0.1321   1.0000
  15.750   1.7795   0.07591   0.07152  -0.1148   0.1212   1.0000
  16.000   1.7574   0.08225   0.07784  -0.1155   0.1088   1.0000
  16.250   1.7371   0.08851   0.08406  -0.1164   0.0960   1.0000
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