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NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M27 AIRFOIL (m27-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.16 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m27-il-1000000-n5.txt
Download as CSV file: xf-m27-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2082   0.09772   0.09452  -0.0130   0.5233   0.0104
  -8.250  -0.2025   0.09451   0.09130  -0.0150   0.5209   0.0107
  -8.000  -0.2068   0.08914   0.08595  -0.0189   0.5193   0.0117
  -7.750  -0.1997   0.08701   0.08382  -0.0203   0.5166   0.0118
  -7.500  -0.1874   0.08471   0.08150  -0.0224   0.5136   0.0119
  -7.250  -0.1743   0.08229   0.07906  -0.0246   0.5108   0.0121
  -7.000  -0.1608   0.07957   0.07630  -0.0270   0.5081   0.0123
  -6.750  -0.1464   0.07669   0.07339  -0.0295   0.5056   0.0126
  -6.500  -0.1311   0.07359   0.07027  -0.0321   0.5036   0.0129
  -6.250  -0.1170   0.06770   0.06431  -0.0367   0.5018   0.0143
  -6.000  -0.0980   0.06573   0.06230  -0.0383   0.4988   0.0144
  -5.750  -0.0781   0.06361   0.06014  -0.0399   0.4956   0.0146
  -5.500  -0.0576   0.06138   0.05785  -0.0417   0.4925   0.0148
  -5.250  -0.0364   0.05893   0.05534  -0.0435   0.4897   0.0151
  -5.000  -0.0145   0.05634   0.05270  -0.0452   0.4878   0.0154
  -4.750   0.0081   0.05364   0.04993  -0.0469   0.4855   0.0157
  -4.500   0.0341   0.04821   0.04433  -0.0496   0.4835   0.0172
  -4.250   0.0569   0.04630   0.04236  -0.0505   0.4805   0.0174
  -4.000   0.0805   0.04473   0.04072  -0.0513   0.4773   0.0176
  -3.500   0.1298   0.04115   0.03700  -0.0528   0.4721   0.0180
  -3.250   0.1551   0.03916   0.03493  -0.0534   0.4698   0.0182
  -3.000   0.1809   0.03717   0.03285  -0.0540   0.4673   0.0185
  -2.750   0.2070   0.03521   0.03078  -0.0544   0.4646   0.0192
  -2.500   0.2335   0.03287   0.02831  -0.0546   0.4619   0.0195
  -2.250   0.2604   0.03035   0.02561  -0.0546   0.4591   0.0199
  -2.000   0.2871   0.02772   0.02280  -0.0544   0.4569   0.0202
  -1.750   0.3142   0.02469   0.01956  -0.0538   0.4547   0.0206
  -1.500   0.3394   0.02168   0.01631  -0.0531   0.4524   0.0209
  -1.250   0.3663   0.02019   0.01468  -0.0529   0.4499   0.0212
  -0.750   0.4181   0.01352   0.00715  -0.0512   0.4451   0.0222
  -0.500   0.4465   0.01274   0.00618  -0.0513   0.4423   0.0225
  -0.250   0.4752   0.01223   0.00556  -0.0515   0.4399   0.0227
   0.000   0.5040   0.01187   0.00512  -0.0518   0.4372   0.0231
   0.250   0.5327   0.01152   0.00468  -0.0520   0.4345   0.0234
   0.500   0.5612   0.01122   0.00431  -0.0523   0.4318   0.0236
   0.750   0.5896   0.01101   0.00403  -0.0525   0.4290   0.0239
   1.000   0.6179   0.01084   0.00381  -0.0527   0.4264   0.0242
   1.250   0.6462   0.01069   0.00365  -0.0529   0.4240   0.0245
   1.500   0.6745   0.01059   0.00352  -0.0531   0.4213   0.0247
   1.750   0.7023   0.01045   0.00336  -0.0532   0.4186   0.0250
   2.000   0.7296   0.01029   0.00318  -0.0533   0.4160   0.0255
   2.250   0.7571   0.01023   0.00311  -0.0534   0.4133   0.0259
   2.500   0.7848   0.01019   0.00307  -0.0536   0.4108   0.0264
   2.750   0.8127   0.01015   0.00304  -0.0538   0.4085   0.0268
   3.000   0.8405   0.01013   0.00303  -0.0540   0.4058   0.0274
   3.250   0.8683   0.01014   0.00304  -0.0542   0.4031   0.0284
   3.500   0.8961   0.01016   0.00306  -0.0545   0.4005   0.0291
   3.750   0.9237   0.01021   0.00309  -0.0547   0.3979   0.0297
   4.000   0.9514   0.01024   0.00313  -0.0550   0.3955   0.0306
   4.250   0.9792   0.01026   0.00317  -0.0553   0.3933   0.0322
   4.500   1.0070   0.01030   0.00323  -0.0556   0.3906   0.0342
   4.750   1.0347   0.01036   0.00330  -0.0558   0.3879   0.0391
   5.000   1.0619   0.01041   0.00344  -0.0561   0.3853   0.0746
   5.250   1.0892   0.01051   0.00356  -0.0564   0.3827   0.0903
   5.500   1.1166   0.01060   0.00369  -0.0567   0.3805   0.1051
   5.750   1.1441   0.01065   0.00382  -0.0570   0.3784   0.1370
   6.000   1.1710   0.01067   0.00399  -0.0573   0.3759   0.2229
   6.250   1.1803   0.00946   0.00426  -0.0537   0.3736   0.9535
   6.500   1.2122   0.00971   0.00452  -0.0550   0.3692   0.9743
   6.750   1.2433   0.00996   0.00475  -0.0562   0.3632   0.9817
   7.000   1.2804   0.01020   0.00498  -0.0588   0.3576   0.9854
   7.500   1.3562   0.01075   0.00550  -0.0647   0.3453   0.9894
   7.750   1.3891   0.01113   0.00583  -0.0666   0.3358   0.9917
   8.000   1.4174   0.01139   0.00608  -0.0674   0.3278   0.9932
   8.250   1.4422   0.01178   0.00641  -0.0677   0.3171   0.9939
   8.500   1.4668   0.01240   0.00692  -0.0683   0.2959   0.9944
   8.750   1.4881   0.01333   0.00769  -0.0686   0.2679   0.9952
   9.000   1.4927   0.01578   0.00972  -0.0677   0.2052   0.9973
   9.250   1.4642   0.01913   0.01285  -0.0627   0.1587   1.0000
   9.500   1.4362   0.02164   0.01532  -0.0565   0.1401   1.0000
   9.750   1.4073   0.02511   0.01869  -0.0517   0.1139   1.0000
  10.000   1.3798   0.02913   0.02262  -0.0481   0.0854   1.0000
  10.250   1.3544   0.03345   0.02688  -0.0454   0.0575   1.0000
  10.500   1.3299   0.03799   0.03137  -0.0432   0.0283   1.0000
  10.750   1.3224   0.04111   0.03449  -0.0420   0.0179   1.0000
  11.000   1.3239   0.04346   0.03689  -0.0413   0.0159   1.0000
  11.250   1.3258   0.04584   0.03931  -0.0407   0.0146   1.0000
  11.500   1.3272   0.04835   0.04187  -0.0402   0.0135   1.0000
  11.750   1.3301   0.05074   0.04432  -0.0398   0.0129   1.0000
  12.000   1.3334   0.05309   0.04672  -0.0394   0.0124   1.0000
  12.250   1.3350   0.05569   0.04937  -0.0390   0.0119   1.0000
  12.500   1.3367   0.05831   0.05204  -0.0387   0.0114   1.0000
  12.750   1.3375   0.06105   0.05483  -0.0385   0.0109   1.0000
  13.000   1.3369   0.06398   0.05781  -0.0382   0.0105   1.0000
  13.250   1.3376   0.06679   0.06067  -0.0380   0.0101   1.0000
  13.500   1.3389   0.06959   0.06353  -0.0379   0.0098   1.0000
  13.750   1.3410   0.07226   0.06626  -0.0378   0.0095   1.0000
  14.000   1.3414   0.07518   0.06923  -0.0377   0.0092   1.0000
  14.250   1.3429   0.07798   0.07208  -0.0377   0.0089   1.0000
  14.500   1.3431   0.08099   0.07515  -0.0377   0.0086   1.0000
  14.750   1.3435   0.08399   0.07819  -0.0378   0.0083   1.0000
  15.000   1.3430   0.08710   0.08136  -0.0379   0.0080   1.0000
  15.250   1.3411   0.09042   0.08473  -0.0380   0.0078   1.0000
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