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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 100,000
Max Cl/Cd: 37.04 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-100000.txt
Download as CSV file: xf-fx74130wp2-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2453   0.12713   0.12250  -0.0819   0.9674   0.0642
 -11.250  -0.2490   0.12521   0.12062  -0.0874   0.9641   0.0649
 -11.000  -0.2501   0.12266   0.11810  -0.0931   0.9615   0.0652
 -10.750  -0.2149   0.11491   0.11028  -0.0888   0.9613   0.0687
 -10.500  -0.2015   0.11132   0.10668  -0.0913   0.9597   0.0718
 -10.250  -0.1296   0.09962   0.09524  -0.0986   0.9454   0.0804
 -10.000  -0.1091   0.09580   0.09138  -0.0983   0.9444   0.0842
  -9.750  -0.1096   0.09335   0.08894  -0.0983   0.9423   0.0874
  -9.500  -0.1342   0.09440   0.09008  -0.0921   0.9376   0.0878
  -9.250  -0.1816   0.09598   0.09137  -0.1021   0.9466   0.0835
  -9.000  -0.1747   0.09301   0.08840  -0.1041   0.9448   0.0875
  -8.750  -0.1845   0.09124   0.08668  -0.1045   0.9417   0.0900
  -8.500  -0.2117   0.09141   0.08693  -0.0994   0.9365   0.0905
  -8.250  -0.2361   0.09062   0.08622  -0.0976   0.9332   0.0913
  -8.000  -0.2604   0.08961   0.08528  -0.0961   0.9308   0.0916
  -7.750  -0.2880   0.08919   0.08490  -0.0920   0.9283   0.0916
  -7.500  -0.3160   0.08914   0.08492  -0.0855   0.9271   0.0912
  -7.250  -0.3434   0.08862   0.08447  -0.0804   0.9266   0.0912
  -7.000  -0.3691   0.08769   0.08356  -0.0766   0.9263   0.0915
  -6.750  -0.3961   0.08669   0.08246  -0.0745   0.9284   0.0923
  -6.500  -0.4258   0.08623   0.08194  -0.0692   0.9314   0.0927
  -6.250  -0.5895   0.09690   0.09316  -0.0278   1.0000   0.0786
  -6.000  -0.5957   0.09312   0.08913  -0.0300   1.0000   0.0793
  -5.750  -0.5890   0.08822   0.08450  -0.0259   1.0000   0.0812
  -5.500  -0.5856   0.08529   0.08160  -0.0240   1.0000   0.0840
  -5.250  -0.5815   0.08193   0.07815  -0.0245   1.0000   0.0877
  -5.000  -0.5741   0.07715   0.07292  -0.0293   1.0000   0.0941
  -4.750  -0.5672   0.07377   0.06967  -0.0274   1.0000   0.0965
  -4.500  -0.5546   0.07093   0.06663  -0.0283   1.0000   0.1050
  -4.250  -0.5436   0.06686   0.06240  -0.0289   1.0000   0.1104
  -4.000  -0.5271   0.06390   0.05911  -0.0305   1.0000   0.1228
  -3.750  -0.5125   0.06149   0.05664  -0.0302   1.0000   0.1335
  -3.500  -0.4986   0.05820   0.05333  -0.0301   1.0000   0.1424
  -1.750  -0.2967   0.03901   0.03036  -0.0332   0.9984   0.0658
  -1.500  -0.2636   0.03724   0.02838  -0.0343   0.9962   0.0619
  -1.250  -0.2313   0.03641   0.02727  -0.0350   0.9944   0.0594
  -1.000  -0.2007   0.03574   0.02639  -0.0356   0.9907   0.0586
  -0.750  -0.1682   0.03550   0.02603  -0.0365   0.9874   0.0598
  -0.500  -0.1348   0.03585   0.02627  -0.0378   0.9848   0.0644
  -0.250  -0.1085   0.03546   0.02597  -0.0383   0.9800   0.0759
   0.000  -0.0760   0.03543   0.02598  -0.0396   0.9754   0.1057
   0.250  -0.0757   0.03317   0.02699  -0.0301   0.9729   1.0000
   0.500  -0.0482   0.03383   0.02727  -0.0313   0.9636   1.0000
   1.000   0.0145   0.03593   0.02881  -0.0352   0.9471   1.0000
   1.250   0.0422   0.03695   0.02965  -0.0366   0.9393   1.0000
   1.500   0.0766   0.03822   0.03073  -0.0391   0.9311   1.0000
   1.750   0.0995   0.03884   0.03121  -0.0395   0.9206   1.0000
   2.000   0.1396   0.04090   0.03310  -0.0431   0.9157   1.0000
   2.250   0.1596   0.04117   0.03329  -0.0429   0.9039   1.0000
   2.500   0.1815   0.04191   0.03396  -0.0432   0.8933   1.0000
   2.750   0.2223   0.04399   0.03592  -0.0467   0.8881   1.0000
   3.000   0.2416   0.04438   0.03627  -0.0465   0.8760   1.0000
   3.250   0.2622   0.04513   0.03698  -0.0466   0.8647   1.0000
   3.500   0.2865   0.04623   0.03805  -0.0473   0.8548   1.0000
   3.750   0.3267   0.04798   0.03976  -0.0504   0.8471   1.0000
   4.000   0.3473   0.04865   0.04042  -0.0503   0.8345   1.0000
   4.250   0.3696   0.04952   0.04130  -0.0506   0.8220   1.0000
   4.750   0.4616   0.04983   0.04161  -0.0545   0.7671   1.0000
   5.000   0.5137   0.04994   0.04175  -0.0572   0.7506   1.0000
   5.250   0.5423   0.05023   0.04211  -0.0575   0.7372   1.0000
   5.500   0.5663   0.05061   0.04255  -0.0574   0.7246   1.0000
   5.750   0.5898   0.05106   0.04307  -0.0573   0.7125   1.0000
   6.000   0.6153   0.05151   0.04359  -0.0574   0.7013   1.0000
   6.250   0.6627   0.05151   0.04375  -0.0597   0.6955   1.0000
   6.500   0.6835   0.05181   0.04416  -0.0591   0.6833   1.0000
   6.750   0.7066   0.05208   0.04454  -0.0588   0.6715   1.0000
   7.000   0.7328   0.05216   0.04476  -0.0587   0.6601   1.0000
   7.250   0.7864   0.05105   0.04390  -0.0608   0.6551   1.0000
   7.500   0.8121   0.05072   0.04374  -0.0603   0.6427   1.0000
   7.750   0.8421   0.04995   0.04316  -0.0599   0.6304   1.0000
   8.000   0.8769   0.04858   0.04200  -0.0596   0.6181   1.0000
   8.250   0.9174   0.04633   0.04005  -0.0592   0.6055   1.0000
   8.500   0.9702   0.04209   0.03615  -0.0586   0.5913   1.0000
   8.750   1.0235   0.03704   0.03146  -0.0573   0.5745   1.0000
   9.000   1.0415   0.03548   0.03015  -0.0544   0.5437   1.0000
   9.250   1.0985   0.02966   0.02376  -0.0513   0.3972   1.0000
   9.500   1.0799   0.03225   0.02514  -0.0459   0.2524   1.0000
   9.750   1.0605   0.03568   0.02759  -0.0417   0.1578   1.0000
  10.000   1.0545   0.03846   0.02985  -0.0386   0.1140   1.0000
  10.250   1.0568   0.04072   0.03185  -0.0362   0.0925   1.0000
  10.500   1.0682   0.04253   0.03359  -0.0345   0.0764   1.0000
  10.750   1.0860   0.04422   0.03522  -0.0332   0.0630   1.0000
  11.000   1.1178   0.04596   0.03691  -0.0326   0.0514   1.0000
  11.250   1.1765   0.04873   0.03974  -0.0340   0.0425   1.0000
  11.500   1.2114   0.05186   0.04337  -0.0338   0.0403   1.0000
  11.750   1.2273   0.05492   0.04682  -0.0327   0.0381   1.0000
  12.000   1.2381   0.05785   0.05002  -0.0315   0.0362   1.0000
  12.250   1.2471   0.06125   0.05367  -0.0303   0.0350   1.0000
  12.500   1.2434   0.06524   0.05812  -0.0281   0.0354   1.0000
  12.750   1.2300   0.06951   0.06284  -0.0256   0.0361   1.0000
  13.000   1.2140   0.07409   0.06783  -0.0235   0.0369   1.0000
  13.250   1.1956   0.07884   0.07293  -0.0218   0.0377   1.0000
  13.500   1.1760   0.08378   0.07817  -0.0207   0.0384   1.0000
  13.750   1.1554   0.08897   0.08363  -0.0202   0.0391   1.0000
  14.000   1.1338   0.09445   0.08935  -0.0204   0.0397   1.0000
  14.250   1.1117   0.10026   0.09536  -0.0213   0.0403   1.0000
  14.500   1.0900   0.10637   0.10166  -0.0229   0.0408   1.0000
  14.750   1.0684   0.11300   0.10845  -0.0254   0.0413   1.0000
  15.000   1.0480   0.12012   0.11569  -0.0287   0.0419   1.0000
  15.250   1.0340   0.12737   0.12302  -0.0319   0.0427   1.0000
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