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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.87 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m23-il-1000000-n5.txt
Download as CSV file: xf-m23-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M23 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4139   0.10073   0.09802   0.0213   0.5754   0.0045
  -7.750  -0.4100   0.09733   0.09461   0.0189   0.5718   0.0046
  -7.500  -0.4052   0.09386   0.09113   0.0163   0.5683   0.0048
  -7.250  -0.3958   0.08988   0.08712   0.0130   0.5650   0.0050
  -7.000  -0.3852   0.08542   0.08265   0.0093   0.5619   0.0053
  -6.750  -0.3749   0.07905   0.07624   0.0043   0.5591   0.0058
  -6.500  -0.3583   0.07558   0.07272   0.0014   0.5551   0.0060
  -6.250  -0.3397   0.07291   0.07000  -0.0010   0.5510   0.0062
  -6.000  -0.3204   0.07005   0.06711  -0.0034   0.5477   0.0065
  -5.750  -0.3002   0.06655   0.06354  -0.0060   0.5442   0.0070
  -5.500  -0.2791   0.05946   0.05633  -0.0105   0.5414   0.0081
  -5.250  -0.2561   0.05689   0.05369  -0.0123   0.5372   0.0084
  -5.000  -0.2325   0.05470   0.05142  -0.0139   0.5335   0.0087
  -4.750  -0.2084   0.05233   0.04898  -0.0153   0.5297   0.0092
  -4.500  -0.1820   0.04592   0.04237  -0.0179   0.5268   0.0111
  -4.250  -0.1568   0.04432   0.04069  -0.0189   0.5228   0.0113
  -4.000  -0.1313   0.04270   0.03899  -0.0197   0.5191   0.0117
  -3.750  -0.1054   0.04085   0.03706  -0.0205   0.5153   0.0123
  -3.500  -0.0760   0.03468   0.03059  -0.0214   0.5123   0.0148
  -3.250  -0.0499   0.03351   0.02933  -0.0218   0.5085   0.0150
  -3.000  -0.0236   0.03256   0.02831  -0.0223   0.5049   0.0154
  -2.750   0.0031   0.03132   0.02699  -0.0226   0.5012   0.0159
  -2.500   0.0306   0.02939   0.02493  -0.0229   0.4973   0.0167
  -2.250   0.0592   0.02636   0.02166  -0.0227   0.4938   0.0179
  -2.000   0.0883   0.02148   0.01638  -0.0219   0.4911   0.0196
  -1.750   0.1154   0.01983   0.01457  -0.0218   0.4881   0.0199
  -1.500   0.1429   0.01823   0.01280  -0.0217   0.4843   0.0202
  -1.250   0.1706   0.01702   0.01144  -0.0217   0.4803   0.0205
  -0.750   0.2264   0.01427   0.00828  -0.0215   0.4738   0.0215
  -0.500   0.2547   0.01331   0.00714  -0.0215   0.4701   0.0221
  -0.250   0.2831   0.01262   0.00631  -0.0215   0.4661   0.0227
   0.000   0.3115   0.01207   0.00562  -0.0217   0.4622   0.0231
   0.250   0.3400   0.01158   0.00503  -0.0218   0.4591   0.0235
   0.500   0.3686   0.01115   0.00452  -0.0219   0.4556   0.0236
   0.750   0.3970   0.01077   0.00406  -0.0221   0.4515   0.0238
   1.000   0.4254   0.01049   0.00371  -0.0223   0.4475   0.0240
   1.250   0.4538   0.01027   0.00346  -0.0224   0.4444   0.0243
   1.500   0.4820   0.00998   0.00313  -0.0226   0.4409   0.0244
   1.750   0.5100   0.00973   0.00285  -0.0227   0.4370   0.0244
   2.000   0.5380   0.00954   0.00262  -0.0228   0.4330   0.0245
   2.250   0.5660   0.00937   0.00244  -0.0229   0.4297   0.0246
   2.500   0.5941   0.00924   0.00232  -0.0231   0.4262   0.0249
   2.750   0.6222   0.00917   0.00224  -0.0233   0.4224   0.0252
   3.000   0.6505   0.00916   0.00221  -0.0235   0.4184   0.0255
   3.250   0.6784   0.00902   0.00207  -0.0237   0.4150   0.0268
   3.500   0.7066   0.00897   0.00202  -0.0239   0.4113   0.0279
   3.750   0.7350   0.00897   0.00203  -0.0242   0.4076   0.0288
   4.000   0.7633   0.00901   0.00207  -0.0245   0.4036   0.0295
   4.250   0.7917   0.00902   0.00210  -0.0248   0.4002   0.0301
   4.500   0.8201   0.00905   0.00215  -0.0251   0.3963   0.0313
   4.750   0.8484   0.00911   0.00222  -0.0255   0.3925   0.0323
   5.000   0.8767   0.00919   0.00229  -0.0258   0.3848   0.0328
   5.250   0.9048   0.00932   0.00239  -0.0262   0.3727   0.0337
   5.750   0.9606   0.00951   0.00271  -0.0269   0.3505   0.1453
   6.250   1.0184   0.00864   0.00338  -0.0286   0.3090   0.9900
   6.500   1.0526   0.00976   0.00408  -0.0314   0.2355   0.9939
   6.750   1.0905   0.01342   0.00658  -0.0377   0.0163   0.9975
   7.000   1.1302   0.01382   0.00702  -0.0410   0.0128   0.9993
   7.250   1.1579   0.01419   0.00741  -0.0416   0.0112   0.9997
   7.500   1.1836   0.01464   0.00789  -0.0419   0.0097   1.0000
   7.750   1.2053   0.01510   0.00839  -0.0414   0.0087   1.0000
   8.000   1.2268   0.01550   0.00882  -0.0408   0.0081   1.0000
   8.250   1.2477   0.01595   0.00929  -0.0402   0.0074   1.0000
   8.500   1.2676   0.01645   0.00981  -0.0394   0.0068   1.0000
   8.750   1.2855   0.01710   0.01050  -0.0385   0.0062   1.0000
   9.000   1.3026   0.01776   0.01120  -0.0374   0.0058   1.0000
   9.250   1.3190   0.01840   0.01191  -0.0363   0.0056   1.0000
   9.500   1.3335   0.01914   0.01270  -0.0350   0.0053   1.0000
   9.750   1.3459   0.01998   0.01359  -0.0336   0.0050   1.0000
  10.000   1.3554   0.02107   0.01474  -0.0325   0.0048   1.0000
  10.250   1.3563   0.02251   0.01624  -0.0304   0.0046   1.0000
  10.500   1.3632   0.02403   0.01779  -0.0296   0.0044   1.0000
  10.750   1.3689   0.02590   0.01972  -0.0291   0.0041   1.0000
  11.000   1.3692   0.02843   0.02236  -0.0286   0.0039   1.0000
  11.250   1.3745   0.03049   0.02449  -0.0283   0.0039   1.0000
  11.500   1.3784   0.03272   0.02681  -0.0280   0.0038   1.0000
  11.750   1.3808   0.03512   0.02928  -0.0277   0.0037   1.0000
  12.000   1.3820   0.03767   0.03191  -0.0274   0.0036   1.0000
  12.250   1.3821   0.04033   0.03466  -0.0271   0.0035   1.0000
  12.500   1.3813   0.04313   0.03754  -0.0269   0.0034   1.0000
  12.750   1.3799   0.04599   0.04048  -0.0266   0.0033   1.0000
  13.000   1.3776   0.04901   0.04358  -0.0265   0.0033   1.0000
  13.250   1.3765   0.05198   0.04662  -0.0264   0.0032   1.0000
  13.500   1.3748   0.05510   0.04982  -0.0265   0.0031   1.0000
  13.750   1.3740   0.05818   0.05299  -0.0266   0.0030   1.0000
  14.000   1.3730   0.06132   0.05620  -0.0268   0.0030   1.0000
  14.250   1.3716   0.06455   0.05950  -0.0270   0.0029   1.0000
  14.500   1.3711   0.06770   0.06273  -0.0272   0.0028   1.0000
  14.750   1.3706   0.07090   0.06599  -0.0276   0.0028   1.0000
  15.000   1.3691   0.07423   0.06939  -0.0279   0.0027   1.0000
  15.250   1.3681   0.07754   0.07276  -0.0283   0.0027   1.0000
  15.500   1.3660   0.08104   0.07634  -0.0288   0.0026   1.0000
  15.750   1.3635   0.08456   0.07993  -0.0292   0.0026   1.0000
  16.000   1.3594   0.08836   0.08381  -0.0298   0.0025   1.0000
  16.250   1.3536   0.09235   0.08789  -0.0303   0.0024   1.0000
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