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NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M26 AIRFOIL (m26-il)
Reynolds number: 200,000
Max Cl/Cd: 78.73 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m26-il-200000.txt
Download as CSV file: xf-m26-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3117   0.12622   0.12203   0.0134   0.6317   0.0204
  -9.000  -0.3057   0.12434   0.12013   0.0108   0.6296   0.0204
  -8.750  -0.3000   0.12247   0.11827   0.0080   0.6275   0.0205
  -8.000  -0.2733   0.10971   0.10554   0.0051   0.6202   0.0209
  -7.750  -0.2650   0.10609   0.10190   0.0043   0.6181   0.0212
  -7.500  -0.2571   0.10301   0.09880   0.0028   0.6161   0.0216
  -7.250  -0.2505   0.10032   0.09607   0.0013   0.6142   0.0221
  -7.000  -0.2405   0.09750   0.09326  -0.0009   0.6121   0.0228
  -6.750  -0.2280   0.09455   0.09031  -0.0037   0.6097   0.0235
  -6.500  -0.2139   0.09160   0.08736  -0.0067   0.6075   0.0242
  -6.250  -0.1967   0.08888   0.08460  -0.0102   0.6055   0.0250
  -6.000  -0.1710   0.08740   0.08304  -0.0163   0.6036   0.0256
  -5.750  -0.1424   0.08617   0.08168  -0.0229   0.6018   0.0258
  -5.250  -0.1100   0.07785   0.07325  -0.0261   0.5989   0.0262
  -5.000  -0.0992   0.07352   0.06896  -0.0258   0.5972   0.0267
  -4.750  -0.0817   0.07038   0.06581  -0.0273   0.5951   0.0277
  -4.500  -0.0595   0.06761   0.06300  -0.0296   0.5929   0.0288
  -4.250  -0.0350   0.06492   0.06023  -0.0321   0.5907   0.0300
  -4.000  -0.0061   0.06260   0.05781  -0.0351   0.5888   0.0318
  -3.750   0.0459   0.06333   0.05820  -0.0411   0.5870   0.0331
  -3.500   0.0633   0.05863   0.05344  -0.0420   0.5856   0.0337
  -3.250   0.0757   0.05475   0.04955  -0.0417   0.5843   0.0346
  -3.000   0.0980   0.05229   0.04704  -0.0428   0.5828   0.0358
  -2.750   0.1248   0.05015   0.04486  -0.0444   0.5807   0.0375
  -2.500   0.1538   0.04823   0.04285  -0.0460   0.5784   0.0398
  -2.250   0.2043   0.04954   0.04378  -0.0488   0.5761   0.0429
  -2.000   0.2213   0.04503   0.03926  -0.0494   0.5745   0.0441
  -1.750   0.2413   0.04254   0.03674  -0.0497   0.5729   0.0455
  -1.500   0.2667   0.04083   0.03492  -0.0502   0.5714   0.0476
  -1.250   0.2948   0.03943   0.03336  -0.0508   0.5699   0.0507
  -1.000   0.3400   0.04110   0.03460  -0.0517   0.5679   0.0550
  -0.750   0.3592   0.03717   0.03076  -0.0526   0.5657   0.0565
  -0.500   0.3819   0.03550   0.02912  -0.0532   0.5636   0.0593
  -0.250   0.4101   0.03453   0.02805  -0.0537   0.5613   0.0642
   0.000   0.4470   0.03463   0.02779  -0.0538   0.5592   0.0690
   0.250   0.4689   0.03238   0.02553  -0.0541   0.5573   0.0710
   0.500   0.4946   0.03127   0.02433  -0.0542   0.5556   0.0747
   0.750   0.5280   0.03143   0.02410  -0.0539   0.5539   0.0831
   1.000   0.5520   0.02987   0.02270  -0.0549   0.5507   0.0859
   1.500   0.6071   0.02855   0.02124  -0.0555   0.5450   0.1016
   1.750   0.6360   0.02805   0.02054  -0.0554   0.5429   0.1124
   2.000   0.6628   0.02736   0.01977  -0.0554   0.5410   0.1207
   2.250   0.6899   0.02669   0.01896  -0.0553   0.5393   0.1304
   2.500   0.7170   0.02658   0.01891  -0.0559   0.5357   0.1440
   2.750   0.7438   0.02640   0.01874  -0.0563   0.5323   0.1612
   3.000   0.7704   0.02593   0.01825  -0.0565   0.5297   0.1875
   3.250   0.7975   0.02534   0.01760  -0.0564   0.5275   0.2148
   3.500   0.8353   0.02397   0.01558  -0.0549   0.5258   0.0744
   3.750   0.8627   0.02353   0.01497  -0.0544   0.5241   0.0714
   4.000   0.8871   0.02396   0.01557  -0.0549   0.5194   0.0707
   4.250   0.9123   0.02396   0.01563  -0.0549   0.5159   0.0718
   4.500   0.9383   0.02374   0.01544  -0.0545   0.5133   0.0749
   4.750   0.9641   0.02353   0.01517  -0.0539   0.5113   0.0810
   5.000   0.9906   0.02342   0.01502  -0.0535   0.5095   0.0999
   5.250   1.0799   0.02313   0.01630  -0.0683   0.5031   1.0000
   5.500   1.1040   0.02334   0.01649  -0.0679   0.4997   1.0000
   5.750   1.1290   0.02333   0.01643  -0.0673   0.4973   1.0000
   6.000   1.1548   0.02310   0.01611  -0.0666   0.4951   1.0000
   6.250   1.1785   0.02273   0.01581  -0.0659   0.4865   1.0000
   6.500   1.2076   0.02113   0.01398  -0.0646   0.4806   1.0000
   6.750   1.2315   0.02091   0.01385  -0.0641   0.4732   1.0000
   7.000   1.2589   0.01979   0.01261  -0.0632   0.4661   1.0000
   7.250   1.2838   0.01904   0.01195  -0.0626   0.4549   1.0000
   7.500   1.3094   0.01815   0.01108  -0.0619   0.4414   1.0000
   7.750   1.3343   0.01738   0.01032  -0.0613   0.4183   1.0000
   8.000   1.3566   0.01723   0.01003  -0.0607   0.3750   1.0000
   8.250   1.3676   0.01850   0.01083  -0.0595   0.3099   1.0000
   8.500   1.3612   0.02130   0.01314  -0.0571   0.2357   1.0000
   8.750   1.3364   0.02509   0.01657  -0.0539   0.1735   1.0000
   9.000   1.3111   0.02881   0.02015  -0.0508   0.1396   1.0000
   9.250   1.2867   0.03334   0.02451  -0.0491   0.0980   1.0000
   9.500   1.2638   0.03804   0.02906  -0.0478   0.0576   1.0000
   9.750   1.2512   0.04185   0.03279  -0.0469   0.0380   1.0000
  10.000   1.2480   0.04476   0.03575  -0.0461   0.0342   1.0000
  10.250   1.2457   0.04761   0.03869  -0.0454   0.0318   1.0000
  10.500   1.2444   0.05038   0.04158  -0.0448   0.0304   1.0000
  10.750   1.2424   0.05327   0.04461  -0.0442   0.0294   1.0000
  11.000   1.2401   0.05631   0.04778  -0.0437   0.0288   1.0000
  11.250   1.2383   0.05939   0.05100  -0.0433   0.0284   1.0000
  11.500   1.2356   0.06265   0.05440  -0.0430   0.0281   1.0000
  11.750   1.2321   0.06608   0.05799  -0.0428   0.0279   1.0000
  12.000   1.2276   0.06971   0.06174  -0.0427   0.0276   1.0000
  12.250   1.2229   0.07340   0.06555  -0.0426   0.0273   1.0000
  12.500   1.2183   0.07711   0.06936  -0.0426   0.0268   1.0000
  12.750   1.2143   0.08076   0.07310  -0.0426   0.0263   1.0000
  13.000   1.2117   0.08418   0.07659  -0.0425   0.0256   1.0000
  13.250   1.2111   0.08726   0.07972  -0.0422   0.0252   1.0000
  13.500   1.2137   0.08978   0.08229  -0.0417   0.0250   1.0000
  13.750   1.2199   0.09164   0.08417  -0.0409   0.0249   1.0000
  14.000   1.2308   0.09262   0.08517  -0.0395   0.0250   1.0000
  14.250   1.2468   0.09269   0.08529  -0.0375   0.0253   1.0000
  14.500   1.2710   0.09134   0.08396  -0.0345   0.0262   1.0000
  14.750   1.3042   0.08878   0.08141  -0.0301   0.0272   1.0000
  15.000   1.3346   0.08744   0.08016  -0.0265   0.0274   1.0000
  15.250   1.0739   0.09965   0.09319  -0.0179   0.0262   1.0000
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