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NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M27 AIRFOIL (m27-il)
Reynolds number: 500,000
Max Cl/Cd: 105.04 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m27-il-500000-n5.txt
Download as CSV file: xf-m27-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M27 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1815   0.09863   0.09487  -0.0150   0.5487   0.0158
  -8.000  -0.1749   0.09554   0.09178  -0.0169   0.5459   0.0160
  -7.500  -0.1643   0.08921   0.08544  -0.0219   0.5407   0.0176
  -7.000  -0.1438   0.08434   0.08053  -0.0255   0.5352   0.0188
  -6.750  -0.1302   0.08107   0.07724  -0.0291   0.5325   0.0203
  -6.250  -0.0990   0.07421   0.07027  -0.0362   0.5267   0.0205
  -6.000  -0.0792   0.07054   0.06649  -0.0405   0.5242   0.0206
  -5.750  -0.0635   0.06725   0.06314  -0.0418   0.5216   0.0207
  -5.500  -0.0482   0.06484   0.06072  -0.0421   0.5190   0.0210
  -5.250  -0.0298   0.06257   0.05843  -0.0433   0.5162   0.0213
  -5.000  -0.0096   0.06030   0.05611  -0.0447   0.5131   0.0218
  -4.750   0.0120   0.05796   0.05369  -0.0463   0.5100   0.0226
  -4.500   0.0448   0.05505   0.05059  -0.0500   0.5073   0.0246
  -4.250   0.0699   0.05219   0.04760  -0.0516   0.5047   0.0247
  -4.000   0.0944   0.04942   0.04473  -0.0528   0.5021   0.0248
  -3.750   0.1188   0.04683   0.04203  -0.0537   0.4995   0.0248
  -3.500   0.1409   0.04386   0.03897  -0.0543   0.4969   0.0250
  -3.250   0.1604   0.04210   0.03716  -0.0544   0.4939   0.0253
  -3.000   0.1829   0.04066   0.03566  -0.0548   0.4910   0.0259
  -2.750   0.2075   0.03913   0.03405  -0.0553   0.4883   0.0267
  -2.500   0.2336   0.03733   0.03215  -0.0557   0.4855   0.0276
  -2.250   0.2684   0.03518   0.02976  -0.0562   0.4828   0.0298
  -2.000   0.2949   0.03323   0.02767  -0.0563   0.4801   0.0299
  -1.500   0.3430   0.02962   0.02382  -0.0563   0.4749   0.0293
  -1.250   0.3695   0.02790   0.02197  -0.0562   0.4725   0.0292
  -1.000   0.3953   0.02632   0.02028  -0.0562   0.4697   0.0280
  -0.750   0.4227   0.02413   0.01789  -0.0557   0.4669   0.0267
  -0.500   0.4505   0.02197   0.01547  -0.0552   0.4643   0.0264
  -0.250   0.4782   0.02007   0.01334  -0.0547   0.4618   0.0266
   0.000   0.5059   0.01745   0.01034  -0.0539   0.4595   0.0267
   0.250   0.5343   0.01582   0.00840  -0.0538   0.4572   0.0275
   0.500   0.5633   0.01467   0.00702  -0.0538   0.4546   0.0276
   0.750   0.5921   0.01403   0.00622  -0.0540   0.4516   0.0278
   1.000   0.6207   0.01360   0.00567  -0.0542   0.4487   0.0282
   1.250   0.6489   0.01329   0.00527  -0.0544   0.4460   0.0286
   1.500   0.6767   0.01308   0.00497  -0.0545   0.4434   0.0290
   1.750   0.7045   0.01289   0.00475  -0.0547   0.4411   0.0294
   2.000   0.7322   0.01274   0.00459  -0.0548   0.4384   0.0298
   2.250   0.7595   0.01260   0.00444  -0.0548   0.4355   0.0301
   2.500   0.7860   0.01242   0.00426  -0.0548   0.4326   0.0312
   2.750   0.8128   0.01238   0.00422  -0.0548   0.4300   0.0324
   3.000   0.8395   0.01237   0.00419  -0.0548   0.4275   0.0332
   3.250   0.8666   0.01234   0.00417  -0.0549   0.4253   0.0341
   3.500   0.8938   0.01233   0.00418  -0.0550   0.4227   0.0351
   3.750   0.9209   0.01235   0.00420  -0.0551   0.4198   0.0362
   4.000   0.9477   0.01238   0.00424  -0.0552   0.4169   0.0386
   4.250   0.9745   0.01245   0.00431  -0.0553   0.4142   0.0426
   4.500   1.0008   0.01252   0.00445  -0.0554   0.4118   0.0719
   4.750   1.0279   0.01257   0.00459  -0.0556   0.4097   0.0942
   5.000   1.0549   0.01265   0.00472  -0.0558   0.4072   0.1097
   5.250   1.0816   0.01272   0.00487  -0.0560   0.4044   0.1412
   5.500   1.1075   0.01277   0.00506  -0.0561   0.4016   0.2238
   6.000   1.1817   0.01216   0.00586  -0.0609   0.3962   0.9836
   6.250   1.2296   0.01239   0.00612  -0.0658   0.3937   0.9869
   6.500   1.2784   0.01265   0.00640  -0.0709   0.3908   0.9927
   6.750   1.3291   0.01289   0.00664  -0.0766   0.3861   0.9963
   7.000   1.3719   0.01314   0.00686  -0.0806   0.3789   0.9991
   7.250   1.4002   0.01333   0.00707  -0.0814   0.3735   0.9997
   7.500   1.4250   0.01360   0.00733  -0.0815   0.3680   1.0000
   7.750   1.4469   0.01385   0.00759  -0.0810   0.3634   1.0000
   8.000   1.4685   0.01409   0.00786  -0.0804   0.3576   1.0000
   8.250   1.4876   0.01448   0.00821  -0.0795   0.3504   1.0000
   8.500   1.5067   0.01482   0.00857  -0.0785   0.3403   1.0000
   8.750   1.5236   0.01526   0.00900  -0.0773   0.3312   1.0000
   9.000   1.5365   0.01586   0.00955  -0.0755   0.3187   1.0000
   9.250   1.5441   0.01664   0.01027  -0.0729   0.3025   1.0000
   9.500   1.5426   0.01768   0.01125  -0.0690   0.2847   1.0000
   9.750   1.5235   0.01897   0.01252  -0.0624   0.2749   1.0000
  10.000   1.5074   0.02079   0.01431  -0.0575   0.2602   1.0000
  10.250   1.4919   0.02323   0.01668  -0.0536   0.2411   1.0000
  10.500   1.4684   0.02674   0.02009  -0.0501   0.2160   1.0000
  10.750   1.4400   0.03113   0.02435  -0.0471   0.1878   1.0000
  11.000   1.4117   0.03583   0.02896  -0.0446   0.1622   1.0000
  11.250   1.3845   0.04066   0.03371  -0.0425   0.1383   1.0000
  11.500   1.3573   0.04579   0.03878  -0.0408   0.1137   1.0000
  11.750   1.3310   0.05115   0.04406  -0.0396   0.0873   1.0000
  12.000   1.3057   0.05663   0.04948  -0.0386   0.0608   1.0000
  12.250   1.2821   0.06214   0.05493  -0.0378   0.0329   1.0000
  12.500   1.2702   0.06643   0.05921  -0.0374   0.0201   1.0000
  12.750   1.2684   0.06960   0.06243  -0.0372   0.0178   1.0000
  13.000   1.2691   0.07247   0.06537  -0.0371   0.0165   1.0000
  13.250   1.2695   0.07542   0.06839  -0.0370   0.0157   1.0000
  13.500   1.2694   0.07845   0.07148  -0.0369   0.0148   1.0000
  13.750   1.2681   0.08169   0.07479  -0.0369   0.0141   1.0000
  14.000   1.2666   0.08497   0.07814  -0.0369   0.0134   1.0000
  14.250   1.2669   0.08803   0.08128  -0.0370   0.0130   1.0000
  14.500   1.2679   0.09102   0.08434  -0.0371   0.0127   1.0000
  14.750   1.2681   0.09415   0.08755  -0.0373   0.0123   1.0000
  15.000   1.2678   0.09738   0.09085  -0.0375   0.0119   1.0000
  15.250   1.2679   0.10055   0.09409  -0.0378   0.0115   1.0000
  15.500   1.2663   0.10397   0.09758  -0.0381   0.0112   1.0000
  15.750   1.2657   0.10728   0.10095  -0.0385   0.0108   1.0000
  16.000   1.2623   0.11103   0.10478  -0.0390   0.0105   1.0000
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