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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 500,000
Max Cl/Cd: 98.75 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m26-il-500000-n5.txt
Download as CSV file: xf-m26-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1750   0.09175   0.08816  -0.0036   0.5126   0.0112
  -7.750  -0.1756   0.08695   0.08337  -0.0048   0.5118   0.0084
  -7.250  -0.2602   0.09617   0.09244   0.0030   0.5128   0.0083
  -7.000  -0.2488   0.09305   0.08932   0.0003   0.5116   0.0081
  -6.750  -0.2360   0.08971   0.08597  -0.0026   0.5104   0.0080
  -6.500  -0.2216   0.08623   0.08247  -0.0058   0.5093   0.0080
  -6.250  -0.2057   0.08262   0.07883  -0.0091   0.5082   0.0081
  -6.000  -0.1879   0.07863   0.07480  -0.0128   0.5072   0.0083
  -5.750  -0.1687   0.07549   0.07163  -0.0158   0.5061   0.0088
  -5.500  -0.1488   0.07335   0.06945  -0.0180   0.5049   0.0094
  -5.250  -0.1272   0.07033   0.06636  -0.0209   0.5038   0.0101
  -5.000  -0.1043   0.06687   0.06284  -0.0240   0.5028   0.0103
  -4.750  -0.0799   0.06334   0.05922  -0.0272   0.5017   0.0106
  -4.500  -0.0512   0.05856   0.05433  -0.0313   0.5009   0.0114
  -4.250  -0.0287   0.05709   0.05284  -0.0326   0.4999   0.0119
  -4.000  -0.0034   0.05500   0.05069  -0.0345   0.4987   0.0131
  -3.750   0.0244   0.05192   0.04753  -0.0369   0.4975   0.0137
  -3.500   0.0582   0.04764   0.04308  -0.0400   0.4963   0.0149
  -3.250   0.0809   0.04644   0.04185  -0.0408   0.4951   0.0155
  -3.000   0.1077   0.04475   0.04009  -0.0421   0.4940   0.0171
  -2.750   0.1373   0.04216   0.03738  -0.0437   0.4929   0.0178
  -2.500   0.1717   0.03916   0.03419  -0.0454   0.4919   0.0195
  -2.250   0.1939   0.03820   0.03320  -0.0460   0.4908   0.0208
  -2.000   0.2312   0.03744   0.03227  -0.0472   0.4898   0.0244
  -1.750   0.2604   0.03533   0.03001  -0.0479   0.4887   0.0245
  -1.500   0.2891   0.03339   0.02792  -0.0484   0.4875   0.0246
  -1.250   0.3187   0.03179   0.02616  -0.0489   0.4863   0.0248
  -1.000   0.3476   0.02999   0.02424  -0.0492   0.4854   0.0248
  -0.750   0.3739   0.02689   0.02097  -0.0496   0.4845   0.0256
  -0.500   0.4000   0.02575   0.01977  -0.0500   0.4835   0.0262
  -0.250   0.4271   0.02476   0.01873  -0.0504   0.4824   0.0271
   0.250   0.4877   0.02373   0.01750  -0.0508   0.4797   0.0333
   0.500   0.5166   0.02256   0.01621  -0.0509   0.4785   0.0334
   0.750   0.5452   0.02133   0.01485  -0.0510   0.4772   0.0334
   1.000   0.5728   0.01852   0.01176  -0.0509   0.4756   0.0276
   1.250   0.6019   0.01727   0.01032  -0.0508   0.4736   0.0278
   1.500   0.6307   0.01620   0.00905  -0.0507   0.4717   0.0281
   1.750   0.6596   0.01516   0.00785  -0.0507   0.4701   0.0282
   2.000   0.6882   0.01456   0.00717  -0.0509   0.4687   0.0292
   2.250   0.7169   0.01390   0.00641  -0.0510   0.4672   0.0293
   2.500   0.7454   0.01327   0.00567  -0.0511   0.4655   0.0288
   2.750   0.7736   0.01283   0.00516  -0.0513   0.4639   0.0285
   3.000   0.8014   0.01250   0.00478  -0.0514   0.4623   0.0285
   3.250   0.8290   0.01226   0.00451  -0.0515   0.4607   0.0286
   3.500   0.8563   0.01207   0.00430  -0.0515   0.4590   0.0290
   3.750   0.8836   0.01196   0.00416  -0.0516   0.4574   0.0297
   4.000   0.9110   0.01187   0.00409  -0.0518   0.4559   0.0307
   4.250   0.9386   0.01181   0.00408  -0.0520   0.4543   0.0317
   4.500   0.9664   0.01177   0.00409  -0.0522   0.4522   0.0325
   4.750   0.9942   0.01177   0.00413  -0.0525   0.4500   0.0333
   5.000   1.0219   0.01175   0.00415  -0.0528   0.4479   0.0353
   5.250   1.0496   0.01173   0.00411  -0.0530   0.4437   0.0360
   5.500   1.0776   0.01169   0.00412  -0.0534   0.4364   0.0368
   5.750   1.1054   0.01169   0.00412  -0.0537   0.4289   0.0386
   6.000   1.1332   0.01169   0.00416  -0.0541   0.4162   0.0438
   6.250   1.1603   0.01175   0.00429  -0.0544   0.3989   0.1095
   6.750   1.2273   0.01294   0.00619  -0.0605   0.2724   0.9941
   7.250   1.2533   0.01971   0.01172  -0.0642   0.0180   1.0000
   7.500   1.2667   0.02053   0.01260  -0.0629   0.0154   1.0000
   7.750   1.2760   0.02166   0.01385  -0.0615   0.0136   1.0000
   8.000   1.2784   0.02309   0.01535  -0.0596   0.0131   1.0000
   8.250   1.2778   0.02471   0.01703  -0.0574   0.0124   1.0000
   8.500   1.2816   0.02648   0.01888  -0.0562   0.0116   1.0000
   8.750   1.2857   0.02846   0.02094  -0.0553   0.0110   1.0000
   9.000   1.2893   0.03061   0.02316  -0.0546   0.0104   1.0000
   9.250   1.2913   0.03297   0.02560  -0.0540   0.0099   1.0000
   9.500   1.2906   0.03566   0.02838  -0.0533   0.0095   1.0000
   9.750   1.2850   0.03886   0.03170  -0.0526   0.0090   1.0000
  10.000   1.2856   0.04142   0.03433  -0.0520   0.0087   1.0000
  10.250   1.2881   0.04380   0.03678  -0.0515   0.0084   1.0000
  10.500   1.2892   0.04633   0.03937  -0.0510   0.0079   1.0000
  10.750   1.2881   0.04909   0.04221  -0.0504   0.0076   1.0000
  11.000   1.2868   0.05198   0.04517  -0.0500   0.0074   1.0000
  11.250   1.2859   0.05488   0.04814  -0.0496   0.0071   1.0000
  11.500   1.2845   0.05792   0.05125  -0.0493   0.0069   1.0000
  11.750   1.2837   0.06092   0.05432  -0.0491   0.0067   1.0000
  12.000   1.2819   0.06409   0.05757  -0.0489   0.0065   1.0000
  12.250   1.2794   0.06739   0.06093  -0.0487   0.0063   1.0000
  12.500   1.2749   0.07097   0.06458  -0.0486   0.0062   1.0000
  12.750   1.2677   0.07491   0.06861  -0.0484   0.0060   1.0000
  13.000   1.2653   0.07829   0.07205  -0.0483   0.0059   1.0000
  13.250   1.2656   0.08136   0.07520  -0.0483   0.0058   1.0000
  13.500   1.2666   0.08433   0.07824  -0.0482   0.0056   1.0000
  13.750   1.2686   0.08715   0.08112  -0.0481   0.0053   1.0000
  14.000   1.2705   0.09002   0.08406  -0.0481   0.0051   1.0000
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