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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 149.74 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-1000000-n5.txt
Download as CSV file: xf-fx74cl5140-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX74_CL5_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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.3241   0.08973   0.08520  -0.1462   0.4721   0.0068
  -9.250   0.3327   0.08772   0.08320  -0.1472   0.4713   0.0068
  -9.000   0.3414   0.08555   0.08104  -0.1480   0.4704   0.0068
  -8.750   0.3504   0.08350   0.07899  -0.1487   0.4693   0.0068
  -8.250   0.3684   0.07910   0.07460  -0.1497   0.4662   0.0068
  -8.000   0.3785   0.07707   0.07257  -0.1499   0.4655   0.0069
  -7.500   0.3963   0.07328   0.06880  -0.1507   0.4633   0.0069
  -7.250   0.4052   0.07146   0.06700  -0.1510   0.4628   0.0070
  -7.000   0.4135   0.06963   0.06520  -0.1512   0.4622   0.0070
  -6.750   0.4215   0.06787   0.06345  -0.1513   0.4615   0.0071
  -6.500   0.4290   0.06622   0.06183  -0.1513   0.4608   0.0073
  -6.250   0.4351   0.06453   0.06017  -0.1510   0.4601   0.0075
  -6.000   0.4392   0.06297   0.05864  -0.1502   0.4594   0.0079
  -5.750   0.4418   0.06151   0.05721  -0.1492   0.4587   0.0079
  -5.500   0.4499   0.05967   0.05540  -0.1498   0.4580   0.0084
  -5.250   0.4599   0.05762   0.05336  -0.1510   0.4572   0.0088
  -5.000   0.4718   0.05532   0.05108  -0.1532   0.4564   0.0089
  -4.750   0.4873   0.05284   0.04861  -0.1565   0.4556   0.0089
  -4.500   0.5055   0.05034   0.04611  -0.1600   0.4548   0.0089
  -4.250   0.5275   0.04765   0.04341  -0.1644   0.4539   0.0090
  -4.000   0.5542   0.04472   0.04046  -0.1699   0.4530   0.0090
  -3.750   0.5844   0.04171   0.03741  -0.1757   0.4521   0.0090
  -3.500   0.6177   0.03871   0.03434  -0.1816   0.4511   0.0090
  -3.250   0.6549   0.03560   0.03115  -0.1879   0.4500   0.0090
  -3.000   0.6955   0.03252   0.02796  -0.1943   0.4488   0.0090
  -2.750   0.7393   0.02943   0.02473  -0.2008   0.4478   0.0090
  -2.500   0.7866   0.02630   0.02146  -0.2074   0.4473   0.0090
  -2.250   0.8356   0.02326   0.01822  -0.2137   0.4467   0.0090
  -2.000   0.8873   0.02026   0.01494  -0.2200   0.4461   0.0090
  -1.750   0.9415   0.01734   0.01169  -0.2272   0.4453   0.0092
  -1.500   0.9794   0.01634   0.01055  -0.2302   0.4445   0.0095
  -1.000   1.0599   0.01429   0.00789  -0.2357   0.4425   0.0117
  -0.750   1.0940   0.01362   0.00718  -0.2375   0.4415   0.0122
  -0.500   1.1270   0.01320   0.00666  -0.2388   0.4405   0.0129
  -0.250   1.1599   0.01284   0.00615  -0.2400   0.4394   0.0149
   0.500   1.2543   0.01208   0.00518  -0.2426   0.4351   0.0134
   0.750   1.2836   0.01207   0.00508  -0.2429   0.4335   0.0114
   1.000   1.3164   0.01185   0.00486  -0.2443   0.4321   0.0109
   1.250   1.3482   0.01173   0.00475  -0.2453   0.4314   0.0107
   1.500   1.3795   0.01165   0.00467  -0.2463   0.4307   0.0105
   1.750   1.4104   0.01161   0.00463  -0.2471   0.4299   0.0105
   2.000   1.4406   0.01160   0.00462  -0.2478   0.4290   0.0105
   2.250   1.4704   0.01161   0.00463  -0.2484   0.4281   0.0107
   2.500   1.4995   0.01164   0.00466  -0.2489   0.4271   0.0112
   2.750   1.5283   0.01169   0.00470  -0.2493   0.4260   0.0121
   3.000   1.5564   0.01176   0.00477  -0.2496   0.4249   0.0139
   3.250   1.5842   0.01184   0.00485  -0.2499   0.4237   0.0166
   3.750   1.6570   0.01149   0.00553  -0.2548   0.4212   0.7165
   4.000   1.6833   0.01162   0.00570  -0.2547   0.4198   0.7472
   4.250   1.7095   0.01177   0.00584  -0.2547   0.4181   0.7495
   4.500   1.7356   0.01193   0.00598  -0.2546   0.4165   0.7514
   5.000   1.7890   0.01213   0.00623  -0.2548   0.4140   0.7556
   5.250   1.8155   0.01225   0.00638  -0.2548   0.4125   0.7577
   5.500   1.8416   0.01237   0.00653  -0.2549   0.4109   0.7600
   5.750   1.8674   0.01250   0.00668  -0.2548   0.4092   0.7625
   6.000   1.8929   0.01265   0.00684  -0.2547   0.4075   0.7651
   6.250   1.9181   0.01281   0.00702  -0.2546   0.4059   0.7679
   6.500   1.9428   0.01298   0.00721  -0.2544   0.4044   0.7708
   6.750   1.9671   0.01317   0.00742  -0.2541   0.4027   0.7742
   7.000   1.9922   0.01332   0.00763  -0.2540   0.4014   0.7781
   7.250   2.0169   0.01348   0.00784  -0.2538   0.3999   0.7825
   7.500   2.0414   0.01365   0.00806  -0.2536   0.3984   0.7873
   7.750   2.0654   0.01382   0.00829  -0.2533   0.3967   0.7935
   8.250   2.1104   0.01422   0.00879  -0.2521   0.3933   0.8103
   8.500   2.1308   0.01446   0.00908  -0.2511   0.3904   0.8250
   8.750   2.1517   0.01468   0.00939  -0.2503   0.3873   0.8607
   9.250   2.1847   0.01503   0.00993  -0.2468   0.3819   1.0000
   9.500   2.2035   0.01537   0.01029  -0.2456   0.3785   1.0000
   9.750   2.2194   0.01581   0.01075  -0.2439   0.3745   1.0000
  10.000   2.2394   0.01611   0.01111  -0.2430   0.3707   1.0000
  10.250   2.2571   0.01651   0.01154  -0.2417   0.3653   1.0000
  10.500   2.2705   0.01710   0.01214  -0.2398   0.3598   1.0000
  10.750   2.2873   0.01756   0.01264  -0.2384   0.3523   1.0000
  11.000   2.2958   0.01844   0.01348  -0.2358   0.3391   1.0000
  11.250   2.2953   0.01985   0.01480  -0.2319   0.3211   1.0000
  11.500   2.2928   0.02147   0.01637  -0.2279   0.3054   1.0000
  11.750   2.2850   0.02353   0.01838  -0.2235   0.2871   1.0000
  12.000   2.2709   0.02621   0.02100  -0.2188   0.2676   1.0000
  12.250   2.2542   0.02938   0.02414  -0.2144   0.2518   1.0000
  12.500   2.2361   0.03305   0.02781  -0.2105   0.2369   1.0000
  12.750   2.2092   0.03804   0.03279  -0.2069   0.2208   1.0000
  13.000   2.1832   0.04355   0.03835  -0.2042   0.2094   1.0000
  13.250   2.1513   0.05032   0.04519  -0.2021   0.1986   1.0000
  13.500   2.1197   0.05752   0.05248  -0.2006   0.1907   1.0000
  13.750   2.0877   0.06508   0.06013  -0.1995   0.1817   1.0000
  14.000   2.0506   0.07356   0.06869  -0.1985   0.1724   1.0000
  14.250   2.0194   0.08143   0.07663  -0.1980   0.1643   1.0000
  14.500   1.9864   0.08971   0.08494  -0.1977   0.1536   1.0000
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