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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 500,000
Max Cl/Cd: 115.74 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m26-il-500000.txt
Download as CSV file: xf-m26-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2027   0.10044   0.09700   0.0017   0.5511   0.0134
  -8.250  -0.1971   0.09738   0.09394   0.0008   0.5496   0.0136
  -8.000  -0.2929   0.10678   0.10319   0.0110   0.5525   0.0131
  -7.750  -0.2854   0.10368   0.10011   0.0098   0.5510   0.0133
  -7.500  -0.2777   0.10080   0.09723   0.0081   0.5494   0.0135
  -7.250  -0.2712   0.09812   0.09456   0.0063   0.5478   0.0137
  -7.000  -0.2605   0.09519   0.09162   0.0039   0.5462   0.0141
  -6.750  -0.2479   0.09215   0.08855   0.0012   0.5447   0.0146
  -6.500  -0.2336   0.08901   0.08540  -0.0017   0.5433   0.0153
  -6.250  -0.2149   0.08592   0.08226  -0.0055   0.5420   0.0161
  -6.000  -0.1914   0.08314   0.07941  -0.0108   0.5406   0.0163
  -5.750  -0.1656   0.08045   0.07662  -0.0163   0.5392   0.0164
  -5.500  -0.1486   0.07626   0.07242  -0.0186   0.5381   0.0165
  -5.250  -0.1370   0.07238   0.06854  -0.0186   0.5369   0.0167
  -5.000  -0.1190   0.06937   0.06551  -0.0203   0.5356   0.0170
  -4.750  -0.0977   0.06656   0.06267  -0.0226   0.5343   0.0175
  -4.500  -0.0743   0.06376   0.05981  -0.0250   0.5329   0.0182
  -4.250  -0.0484   0.06094   0.05691  -0.0276   0.5314   0.0194
  -4.000  -0.0068   0.05901   0.05482  -0.0324   0.5298   0.0204
  -3.750   0.0284   0.05662   0.05226  -0.0357   0.5284   0.0205
  -3.500   0.0541   0.03407   0.03001  -0.0361   0.5257   0.0210
  -3.250   0.0728   0.03142   0.02729  -0.0367   0.5244   0.0214
  -3.000   0.0955   0.02907   0.02489  -0.0378   0.5232   0.0221
  -2.750   0.1204   0.02679   0.02254  -0.0390   0.5221   0.0230
  -2.500   0.1554   0.02538   0.02100  -0.0408   0.5207   0.0255
  -2.250   0.1890   0.02379   0.01924  -0.0422   0.5193   0.0258
  -2.000   0.2165   0.02181   0.01714  -0.0429   0.5179   0.0259
  -1.750   0.2362   0.01828   0.01351  -0.0434   0.5168   0.0264
  -1.500   0.2575   0.01658   0.01177  -0.0436   0.5155   0.0270
  -1.250   0.2817   0.01523   0.01035  -0.0440   0.5142   0.0278
  -1.000   0.3081   0.01400   0.00900  -0.0444   0.5129   0.0289
  -0.750   0.3357   0.01287   0.00774  -0.0447   0.5115   0.0305
  -0.500   0.3712   0.01269   0.00733  -0.0448   0.5102   0.0330
  -0.250   0.3995   0.01189   0.00636  -0.0448   0.5087   0.0332
   0.000   0.4375   0.02559   0.01953  -0.0462   0.5090   0.0340
   0.250   0.4631   0.02438   0.01829  -0.0467   0.5078   0.0349
   0.500   0.4906   0.02335   0.01722  -0.0470   0.5062   0.0360
   0.750   0.5190   0.02238   0.01617  -0.0472   0.5042   0.0376
   1.000   0.5486   0.02144   0.01512  -0.0472   0.5021   0.0405
   1.250   0.5810   0.02138   0.01485  -0.0468   0.5003   0.0430
   1.500   0.6064   0.01927   0.01266  -0.0472   0.4987   0.0460
   1.750   0.6342   0.01873   0.01203  -0.0474   0.4971   0.0492
   2.000   0.6652   0.01923   0.01232  -0.0472   0.4955   0.0551
   2.250   0.6909   0.01762   0.01066  -0.0476   0.4938   0.0594
   2.500   0.7196   0.01722   0.01024  -0.0478   0.4924   0.0652
   2.750   0.7482   0.01655   0.00950  -0.0480   0.4907   0.0717
   3.000   0.7764   0.01617   0.00915  -0.0483   0.4889   0.0769
   3.250   0.8049   0.01570   0.00861  -0.0484   0.4870   0.0860
   3.500   0.8333   0.01526   0.00813  -0.0486   0.4851   0.0894
   3.750   0.8630   0.01366   0.00618  -0.0475   0.4835   0.0432
   4.000   0.8895   0.01330   0.00577  -0.0473   0.4819   0.0442
   4.250   0.9163   0.01317   0.00562  -0.0473   0.4802   0.0454
   4.500   0.9435   0.01317   0.00564  -0.0473   0.4783   0.0455
   4.750   0.9711   0.01307   0.00562  -0.0476   0.4763   0.0468
   5.000   0.9988   0.01304   0.00565  -0.0478   0.4740   0.0499
   5.250   1.0267   0.01296   0.00561  -0.0480   0.4711   0.0587
   5.500   1.0542   0.01267   0.00549  -0.0481   0.4669   0.1647
   5.750   1.1491   0.01116   0.00545  -0.0633   0.4558   1.0000
   6.000   1.1748   0.01107   0.00529  -0.0630   0.4495   1.0000
   6.250   1.2009   0.01094   0.00525  -0.0630   0.4414   1.0000
   6.500   1.2268   0.01084   0.00515  -0.0629   0.4295   1.0000
   6.750   1.2523   0.01082   0.00504  -0.0628   0.3988   1.0000
   7.000   1.2709   0.01250   0.00606  -0.0631   0.2963   1.0000
   7.250   1.2646   0.01735   0.00974  -0.0622   0.0965   1.0000
   7.500   1.2652   0.01969   0.01181  -0.0602   0.0261   1.0000
   7.750   1.2774   0.02064   0.01282  -0.0588   0.0217   1.0000
   8.000   1.2868   0.02178   0.01405  -0.0575   0.0203   1.0000
   8.250   1.2863   0.02341   0.01578  -0.0554   0.0197   1.0000
   8.500   1.2831   0.02523   0.01769  -0.0529   0.0191   1.0000
   8.750   1.2840   0.02729   0.01984  -0.0516   0.0185   1.0000
   9.000   1.2852   0.02958   0.02224  -0.0507   0.0179   1.0000
   9.250   1.2852   0.03212   0.02487  -0.0500   0.0174   1.0000
   9.500   1.2836   0.03487   0.02771  -0.0493   0.0170   1.0000
   9.750   1.2801   0.03785   0.03079  -0.0486   0.0165   1.0000
  10.000   1.2743   0.04110   0.03413  -0.0479   0.0160   1.0000
  10.250   1.2656   0.04466   0.03779  -0.0471   0.0156   1.0000
  10.500   1.2539   0.04856   0.04179  -0.0464   0.0152   1.0000
  10.750   1.2416   0.05262   0.04596  -0.0458   0.0149   1.0000
  11.000   1.2404   0.05557   0.04898  -0.0454   0.0147   1.0000
  11.250   1.2402   0.05847   0.05194  -0.0450   0.0146   1.0000
  11.500   1.2395   0.06144   0.05498  -0.0447   0.0144   1.0000
  11.750   1.2385   0.06447   0.05810  -0.0444   0.0142   1.0000
  12.000   1.2381   0.06741   0.06110  -0.0440   0.0140   1.0000
  12.250   1.2382   0.07030   0.06403  -0.0436   0.0139   1.0000
  12.500   1.2393   0.07301   0.06680  -0.0432   0.0137   1.0000
  12.750   1.2421   0.07539   0.06922  -0.0425   0.0136   1.0000
  13.000   1.2473   0.07733   0.07119  -0.0417   0.0136   1.0000
  13.250   1.2553   0.07886   0.07274  -0.0407   0.0134   1.0000
  13.500   1.2645   0.08031   0.07422  -0.0398   0.0130   1.0000
  13.750   1.2752   0.08144   0.07539  -0.0387   0.0126   1.0000
  14.000   1.2945   0.08079   0.07476  -0.0360   0.0130   1.0000
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