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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 100,000
Max Cl/Cd: 41.42 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m26-il-100000-n5.txt
Download as CSV file: xf-m26-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M26 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2726   0.12423   0.11898   0.0010   0.6186   0.0247
  -8.500  -0.2658   0.12202   0.11675  -0.0018   0.6157   0.0248
  -8.250  -0.2601   0.11989   0.11463  -0.0045   0.6131   0.0248
  -8.000  -0.2514   0.11758   0.11229  -0.0075   0.6108   0.0248
  -7.500  -0.2312   0.10611   0.10075  -0.0063   0.6068   0.0254
  -7.250  -0.2211   0.10199   0.09665  -0.0070   0.6043   0.0258
  -7.000  -0.2104   0.09864   0.09330  -0.0086   0.6019   0.0263
  -6.750  -0.1989   0.09555   0.09020  -0.0106   0.5996   0.0270
  -6.500  -0.1861   0.09262   0.08723  -0.0129   0.5973   0.0281
  -6.250  -0.1717   0.08979   0.08435  -0.0155   0.5952   0.0296
  -6.000  -0.1548   0.08711   0.08159  -0.0186   0.5933   0.0312
  -5.750  -0.1317   0.08519   0.07955  -0.0233   0.5913   0.0326
  -5.500  -0.1017   0.08414   0.07840  -0.0296   0.5886   0.0333
  -5.250  -0.0733   0.08245   0.07658  -0.0345   0.5862   0.0335
  -5.000  -0.0496   0.07930   0.07334  -0.0376   0.5841   0.0338
  -4.750  -0.0481   0.07267   0.06680  -0.0353   0.5824   0.0349
  -4.500  -0.0331   0.06921   0.06330  -0.0358   0.5807   0.0365
  -4.250  -0.0116   0.06643   0.06041  -0.0377   0.5791   0.0382
  -4.000   0.0126   0.06383   0.05768  -0.0399   0.5776   0.0403
  -3.750   0.0423   0.06171   0.05540  -0.0429   0.5756   0.0436
  -3.500   0.0919   0.06206   0.05541  -0.0487   0.5730   0.0459
  -3.250   0.1015   0.05700   0.05043  -0.0483   0.5708   0.0470
  -3.000   0.1216   0.05417   0.04754  -0.0490   0.5686   0.0490
  -2.750   0.1471   0.05202   0.04526  -0.0502   0.5667   0.0519
  -2.500   0.1974   0.05348   0.04620  -0.0538   0.5650   0.0579
  -2.250   0.2107   0.04880   0.04156  -0.0538   0.5636   0.0592
  -2.000   0.2317   0.04632   0.03899  -0.0541   0.5623   0.0615
  -1.750   0.2590   0.04470   0.03726  -0.0551   0.5602   0.0651
  -1.500   0.3044   0.04618   0.03829  -0.0571   0.5575   0.0706
  -1.250   0.3225   0.04237   0.03453  -0.0577   0.5552   0.0721
  -1.000   0.3442   0.04035   0.03249  -0.0580   0.5532   0.0765
  -0.750   0.3826   0.04119   0.03291  -0.0588   0.5514   0.0844
  -0.250   0.4304   0.03686   0.02838  -0.0594   0.5483   0.0878
   0.750   0.5427   0.03352   0.02453  -0.0613   0.5390   0.1022
   1.000   0.5701   0.03294   0.02380  -0.0615   0.5367   0.1153
   1.250   0.5976   0.03206   0.02278  -0.0616   0.5348   0.1170
   1.500   0.6346   0.03022   0.02027  -0.0606   0.5332   0.0571
   1.750   0.6622   0.02942   0.01930  -0.0605   0.5317   0.0559
   2.000   0.6891   0.02922   0.01910  -0.0612   0.5280   0.0548
   2.250   0.7164   0.02890   0.01870  -0.0615   0.5247   0.0539
   2.500   0.7443   0.02846   0.01813  -0.0616   0.5220   0.0534
   2.750   0.7726   0.02797   0.01749  -0.0616   0.5197   0.0534
   3.000   0.8015   0.02749   0.01686  -0.0616   0.5179   0.0539
   3.250   0.8331   0.02730   0.01650  -0.0623   0.5159   0.0578
   3.500   0.8588   0.02784   0.01722  -0.0634   0.5111   0.0610
   3.750   0.8834   0.02795   0.01731  -0.0633   0.5078   0.0624
   4.000   0.9074   0.02790   0.01719  -0.0627   0.5054   0.0643
   4.250   0.9320   0.02779   0.01698  -0.0621   0.5034   0.0670
   4.500   0.9575   0.02768   0.01675  -0.0615   0.5017   0.0710
   4.750   0.9762   0.02886   0.01811  -0.0618   0.4962   0.0779
   5.000   0.9984   0.02936   0.01869  -0.0616   0.4925   0.0993
   5.250   1.0187   0.02891   0.01898  -0.0608   0.4900   0.5816
   5.750   1.1180   0.02904   0.01974  -0.0706   0.4843   1.0000
   6.000   1.1313   0.03055   0.02141  -0.0701   0.4782   1.0000
   6.250   1.1532   0.03088   0.02176  -0.0695   0.4753   1.0000
   6.500   1.1778   0.03088   0.02177  -0.0688   0.4732   1.0000
   6.750   1.2040   0.03073   0.02164  -0.0682   0.4716   1.0000
   7.000   1.2033   0.03326   0.02444  -0.0670   0.4620   1.0000
   7.250   1.2406   0.03064   0.02173  -0.0660   0.4538   1.0000
   7.500   1.2603   0.03043   0.02160  -0.0649   0.4451   1.0000
   7.750   1.2720   0.03095   0.02227  -0.0636   0.4346   1.0000
   8.000   1.2851   0.03113   0.02258  -0.0622   0.4221   1.0000
   8.250   1.2816   0.03295   0.02452  -0.0606   0.4076   1.0000
   8.500   1.2663   0.03599   0.02763  -0.0586   0.3973   1.0000
   8.750   1.2548   0.03918   0.03087  -0.0574   0.3847   1.0000
   9.000   1.2454   0.04245   0.03418  -0.0565   0.3695   1.0000
   9.250   1.2640   0.04217   0.03377  -0.0553   0.3421   1.0000
   9.500   1.2719   0.04281   0.03398  -0.0536   0.2985   1.0000
   9.750   1.2613   0.04613   0.03713  -0.0523   0.2694   1.0000
  10.000   1.2471   0.04995   0.04075  -0.0512   0.2358   1.0000
  10.500   1.2013   0.05979   0.04996  -0.0493   0.1454   1.0000
  10.750   1.1791   0.06504   0.05491  -0.0487   0.0968   1.0000
  11.000   1.1589   0.07030   0.05990  -0.0483   0.0448   1.0000
  11.250   1.1488   0.07456   0.06406  -0.0480   0.0331   1.0000
  11.500   1.1465   0.07796   0.06756  -0.0478   0.0293   1.0000
  11.750   1.1464   0.08115   0.07088  -0.0477   0.0277   1.0000
  12.000   1.1460   0.08444   0.07432  -0.0476   0.0265   1.0000
  12.250   1.1447   0.08790   0.07794  -0.0476   0.0255   1.0000
  12.500   1.1424   0.09157   0.08176  -0.0478   0.0247   1.0000
  12.750   1.1388   0.09549   0.08584  -0.0480   0.0237   1.0000
  13.000   1.1334   0.09972   0.09021  -0.0484   0.0228   1.0000
  13.250   1.1271   0.10416   0.09480  -0.0489   0.0219   1.0000
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