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FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)
Reynolds number: 100,000
Max Cl/Cd: 41.74 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74modsm-il-100000.txt
Download as CSV file: xf-fx74modsm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-Cl5-140 MOD  (smoothed)                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.1944   0.10914   0.10454  -0.1208   0.8841   0.0404
  -9.000   0.2101   0.10850   0.10381  -0.1272   0.8710   0.0409
  -8.750   0.2242   0.10760   0.10283  -0.1327   0.8574   0.0411
  -8.500   0.2509   0.09897   0.09413  -0.1318   0.8470   0.0422
  -8.250   0.2693   0.09514   0.09020  -0.1329   0.8352   0.0434
  -8.000   0.2849   0.09244   0.08740  -0.1346   0.8241   0.0448
  -7.750   0.2975   0.09023   0.08512  -0.1359   0.8127   0.0462
  -7.500   0.3076   0.08836   0.08321  -0.1369   0.8016   0.0477
  -7.250   0.3191   0.08654   0.08131  -0.1384   0.7922   0.0493
  -7.000   0.3269   0.08551   0.08026  -0.1400   0.7822   0.0508
  -6.750   0.3289   0.08586   0.08062  -0.1418   0.7726   0.0517
  -6.500   0.3399   0.08604   0.08076  -0.1473   0.7645   0.0522
  -6.250   0.3497   0.08389   0.07865  -0.1494   0.7562   0.0527
  -6.000   0.3608   0.07828   0.07297  -0.1433   0.7503   0.0544
  -5.750   0.3725   0.07600   0.07067  -0.1427   0.7434   0.0565
  -5.500   0.3833   0.07428   0.06895  -0.1434   0.7361   0.0592
  -5.250   0.3996   0.07268   0.06727  -0.1467   0.7304   0.0630
  -5.000   0.4316   0.07339   0.06800  -0.1626   0.7219   0.0659
  -4.750   0.4359   0.06920   0.06379  -0.1576   0.7174   0.0673
  -4.500   0.4402   0.06707   0.06170  -0.1535   0.7113   0.0694
  -4.250   0.4540   0.06522   0.05984  -0.1540   0.7050   0.0729
  -3.750   0.5172   0.06064   0.05517  -0.1714   0.6932   0.0826
  -3.500   0.5237   0.05874   0.05328  -0.1673   0.6883   0.0857
  -3.250   0.5918   0.05497   0.04922  -0.1857   0.6841   0.0983
  -3.000   0.5861   0.05409   0.04851  -0.1795   0.6773   0.1006
  -2.750   0.6349   0.05115   0.04540  -0.1897   0.6721   0.1155
  -2.500   0.6725   0.04864   0.04274  -0.1945   0.6684   0.1329
  -2.250   0.6958   0.04742   0.04156  -0.1974   0.6617   0.1491
  -2.000   0.7435   0.04538   0.03934  -0.2052   0.6567   0.1805
  -1.750   0.7800   0.04347   0.03730  -0.2084   0.6531   0.2137
  -0.750   0.9906   0.03501   0.02773  -0.2379   0.6327   0.2015
  -0.500   1.0601   0.03253   0.02403  -0.2452   0.6276   0.1048
  -0.250   1.1006   0.03191   0.02282  -0.2471   0.6237   0.0979
   0.000   1.1365   0.03147   0.02206  -0.2484   0.6203   0.0970
   0.250   1.1534   0.03193   0.02260  -0.2471   0.6143   0.0964
   0.500   1.1829   0.03175   0.02231  -0.2475   0.6101   0.0972
   0.750   1.2176   0.03122   0.02179  -0.2487   0.6068   0.1058
   1.000   1.2406   0.03180   0.02238  -0.2483   0.6021   0.1149
   1.250   1.2628   0.03249   0.02313  -0.2480   0.5967   0.1330
   1.500   1.2864   0.03135   0.02363  -0.2468   0.5935   0.8630
   1.750   1.3144   0.03149   0.02338  -0.2464   0.5906   1.0000
   2.000   1.3256   0.03314   0.02501  -0.2445   0.5852   1.0000
   2.250   1.3431   0.03431   0.02609  -0.2434   0.5801   1.0000
   2.500   1.3740   0.03458   0.02614  -0.2440   0.5769   1.0000
   2.750   1.4079   0.03477   0.02609  -0.2450   0.5743   1.0000
   3.000   1.3964   0.03796   0.02952  -0.2404   0.5675   1.0000
   3.250   1.4148   0.03904   0.03054  -0.2394   0.5632   1.0000
   3.500   1.4493   0.03901   0.03033  -0.2404   0.5605   1.0000
   3.750   1.4871   0.03886   0.02999  -0.2418   0.5583   1.0000
   4.000   1.2787   0.05807   0.05026  -0.2186   0.5375   1.0000
   4.250   1.3460   0.05447   0.04639  -0.2211   0.5381   1.0000
   4.500   1.4269   0.05053   0.04217  -0.2260   0.5391   1.0000
   4.750   1.5417   0.04465   0.03583  -0.2357   0.5421   1.0000
   5.000   1.3740   0.06052   0.05234  -0.2166   0.5261   1.0000
   5.250   1.4385   0.05733   0.04899  -0.2191   0.5263   1.0000
   5.500   1.5144   0.05389   0.04535  -0.2237   0.5267   1.0000
   5.750   1.0244   0.11760   0.11079  -0.2105   0.5136   1.0000
   6.000   1.0423   0.11768   0.11072  -0.2089   0.4994   1.0000
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