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FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 74-CL6-140 (fx74cl6140-il)
Reynolds number: 100,000
Max Cl/Cd: 40.67 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl6140-il-100000-n5.txt
Download as CSV file: xf-fx74cl6140-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0162   0.11451   0.10777  -0.0719   0.6020   0.0394
 -10.000  -0.0113   0.11235   0.10559  -0.0739   0.5990   0.0400
  -9.750  -0.0081   0.11032   0.10358  -0.0761   0.5958   0.0402
  -9.500   0.0003   0.10734   0.10062  -0.0773   0.5924   0.0405
  -9.250   0.0150   0.10387   0.09712  -0.0772   0.5886   0.0413
  -9.000   0.0252   0.10122   0.09444  -0.0779   0.5857   0.0423
  -8.750   0.0338   0.09874   0.09192  -0.0790   0.5832   0.0433
  -8.500   0.0417   0.09630   0.08949  -0.0803   0.5807   0.0444
  -8.250   0.0477   0.09395   0.08717  -0.0819   0.5782   0.0456
  -8.000   0.0477   0.09203   0.08531  -0.0847   0.5759   0.0465
  -7.750   0.0492   0.08991   0.08323  -0.0871   0.5736   0.0468
  -7.500   0.0623   0.08657   0.07989  -0.0869   0.5711   0.0473
  -7.250   0.0756   0.08383   0.07712  -0.0866   0.5687   0.0483
  -7.000   0.0845   0.08144   0.07472  -0.0872   0.5665   0.0495
  -6.750   0.0897   0.07928   0.07255  -0.0883   0.5646   0.0524
  -6.500   0.0859   0.07756   0.07092  -0.0915   0.5627   0.0539
  -6.250   0.0912   0.07463   0.06805  -0.0992   0.5605   0.0544
  -6.000   0.1064   0.07219   0.06563  -0.0928   0.5576   0.0568
  -5.750   0.1174   0.06982   0.06327  -0.0946   0.5553   0.0591
  -5.500   0.1326   0.06589   0.05923  -0.1089   0.5535   0.0633
  -5.250   0.1457   0.06256   0.05591  -0.1092   0.5515   0.0642
  -5.000   0.1605   0.06007   0.05340  -0.1090   0.5497   0.0654
  -4.750   0.1784   0.05737   0.05063  -0.1111   0.5480   0.0669
  -4.250   0.2363   0.04526   0.03788  -0.1245   0.5447   0.0341
  -4.000   0.2621   0.04233   0.03479  -0.1271   0.5423   0.0328
  -3.750   0.2933   0.03849   0.03059  -0.1306   0.5399   0.0312
  -3.500   0.3263   0.03498   0.02660  -0.1336   0.5376   0.0307
  -3.250   0.3563   0.03317   0.02447  -0.1352   0.5353   0.0324
  -3.000   0.3888   0.03095   0.02175  -0.1369   0.5333   0.0333
  -2.750   0.4210   0.02906   0.01936  -0.1382   0.5316   0.0333
  -2.500   0.4525   0.02756   0.01739  -0.1389   0.5300   0.0337
  -2.250   0.4824   0.02642   0.01590  -0.1393   0.5283   0.0343
  -2.000   0.5105   0.02558   0.01493  -0.1395   0.5259   0.0352
  -1.750   0.5379   0.02510   0.01443  -0.1396   0.5234   0.0377
  -1.500   0.5657   0.02459   0.01379  -0.1396   0.5210   0.0407
  -1.250   0.5932   0.02416   0.01335  -0.1396   0.5188   0.0433
  -1.000   0.6212   0.02380   0.01290  -0.1396   0.5169   0.0466
  -0.750   0.6493   0.02357   0.01265  -0.1398   0.5152   0.0533
  -0.500   0.6779   0.02337   0.01242  -0.1400   0.5137   0.0657
  -0.250   0.7073   0.02311   0.01225  -0.1404   0.5122   0.1056
   0.000   0.7335   0.02195   0.01284  -0.1411   0.5099   0.5931
   0.250   0.7508   0.02226   0.01335  -0.1384   0.5074   0.7637
   0.500   0.7649   0.02237   0.01355  -0.1350   0.5052   0.8288
   0.750   0.7793   0.02238   0.01362  -0.1319   0.5032   0.8774
   1.000   0.8014   0.02231   0.01357  -0.1304   0.5013   1.0000
   1.250   0.8316   0.02268   0.01375  -0.1313   0.4993   1.0000
   1.500   0.8620   0.02302   0.01390  -0.1321   0.4975   1.0000
   1.750   0.8924   0.02335   0.01404  -0.1329   0.4959   1.0000
   2.000   0.9224   0.02375   0.01427  -0.1336   0.4943   1.0000
   2.250   0.9468   0.02448   0.01504  -0.1338   0.4916   1.0000
   2.500   0.9719   0.02517   0.01573  -0.1341   0.4889   1.0000
   2.750   0.9978   0.02575   0.01628  -0.1343   0.4863   1.0000
   3.000   1.0246   0.02625   0.01671  -0.1346   0.4840   1.0000
   3.250   1.0520   0.02668   0.01707  -0.1350   0.4820   1.0000
   3.500   1.0798   0.02710   0.01742  -0.1353   0.4804   1.0000
   3.750   1.1080   0.02750   0.01773  -0.1356   0.4789   1.0000
   4.000   1.1359   0.02793   0.01807  -0.1360   0.4774   1.0000
   4.250   1.1509   0.02923   0.01958  -0.1351   0.4734   1.0000
   4.500   1.1707   0.03019   0.02061  -0.1347   0.4703   1.0000
   4.750   1.1929   0.03096   0.02140  -0.1345   0.4679   1.0000
   5.000   1.2171   0.03153   0.02196  -0.1344   0.4658   1.0000
   5.250   1.2432   0.03194   0.02237  -0.1344   0.4640   1.0000
   5.500   1.2709   0.03225   0.02263  -0.1346   0.4625   1.0000
   5.750   1.2994   0.03254   0.02287  -0.1349   0.4612   1.0000
   6.000   1.2916   0.03544   0.02611  -0.1320   0.4553   1.0000
   6.250   1.3041   0.03676   0.02753  -0.1309   0.4519   1.0000
   6.500   1.3247   0.03745   0.02826  -0.1304   0.4495   1.0000
   6.750   1.3494   0.03784   0.02866  -0.1302   0.4478   1.0000
   7.000   1.3761   0.03814   0.02896  -0.1302   0.4464   1.0000
   7.250   1.4046   0.03835   0.02919  -0.1304   0.4452   1.0000
   7.750   1.3369   0.04663   0.03786  -0.1207   0.4316   1.0000
   8.000   1.3644   0.04670   0.03798  -0.1206   0.4305   1.0000
   8.250   1.3909   0.04690   0.03820  -0.1205   0.4294   1.0000
   9.250   1.1554   0.08521   0.07695  -0.1186   0.3768   1.0000
   9.500   1.1728   0.08623   0.07801  -0.1183   0.3742   1.0000
   9.750   1.1937   0.08680   0.07864  -0.1179   0.3726   1.0000
  10.000   1.2156   0.08722   0.07911  -0.1174   0.3714   1.0000
  10.500   1.2069   0.09514   0.08717  -0.1181   0.3584   1.0000
  10.750   1.2291   0.09545   0.08756  -0.1177   0.3572   1.0000
  11.250   1.2230   0.10318   0.09544  -0.1186   0.3444   1.0000
  11.500   1.2452   0.10341   0.09574  -0.1181   0.3431   1.0000
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