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NACA M12 (nacam12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M12 (nacam12-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.29 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacam12-il-1000000.txt
Download as CSV file: xf-nacam12-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M12                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.0039   0.05301   0.05070  -0.0517   1.0000   0.0187
 -14.000  -1.0365   0.04588   0.04331  -0.0554   1.0000   0.0187
 -13.750  -1.0523   0.04204   0.03927  -0.0553   1.0000   0.0189
 -13.500  -1.0626   0.03921   0.03627  -0.0537   1.0000   0.0191
 -13.250  -1.0686   0.03703   0.03391  -0.0513   1.0000   0.0193
 -13.000  -1.0709   0.03530   0.03202  -0.0484   1.0000   0.0195
 -12.750  -1.0644   0.03390   0.03046  -0.0464   1.0000   0.0197
 -12.500  -1.0527   0.03285   0.02927  -0.0449   1.0000   0.0199
 -12.250  -1.0582   0.02955   0.02564  -0.0418   1.0000   0.0203
 -12.000  -1.0482   0.02788   0.02387  -0.0401   1.0000   0.0206
 -11.750  -1.0306   0.02715   0.02310  -0.0389   1.0000   0.0209
 -11.500  -1.0113   0.02664   0.02257  -0.0380   1.0000   0.0212
 -11.250  -0.9921   0.02610   0.02198  -0.0369   1.0000   0.0215
 -11.000  -0.9732   0.02551   0.02133  -0.0358   1.0000   0.0219
 -10.750  -0.9555   0.02475   0.02050  -0.0344   1.0000   0.0222
 -10.500  -0.9388   0.02391   0.01955  -0.0328   1.0000   0.0226
 -10.250  -0.9226   0.02308   0.01862  -0.0311   1.0000   0.0230
 -10.000  -0.9065   0.02233   0.01776  -0.0292   1.0000   0.0233
  -9.750  -0.8906   0.02174   0.01708  -0.0272   1.0000   0.0236
  -9.500  -0.8748   0.02140   0.01666  -0.0250   1.0000   0.0239
  -9.250  -0.8455   0.02012   0.01520  -0.0261   0.9982   0.0244
  -9.000  -0.8174   0.01836   0.01334  -0.0271   0.9962   0.0250
  -8.750  -0.7851   0.01757   0.01251  -0.0285   0.9944   0.0254
  -8.500  -0.7528   0.01692   0.01182  -0.0298   0.9923   0.0259
  -8.250  -0.7208   0.01634   0.01119  -0.0311   0.9891   0.0264
  -8.000  -0.6879   0.01580   0.01060  -0.0324   0.9858   0.0270
  -7.750  -0.6552   0.01518   0.00993  -0.0337   0.9825   0.0275
  -7.500  -0.6270   0.01462   0.00932  -0.0339   0.9748   0.0279
  -7.250  -0.5969   0.01411   0.00874  -0.0345   0.9684   0.0283
  -7.000  -0.5707   0.01369   0.00827  -0.0342   0.9577   0.0286
  -6.750  -0.5448   0.01334   0.00787  -0.0338   0.9468   0.0289
  -6.500  -0.5215   0.01262   0.00707  -0.0329   0.9352   0.0294
  -6.250  -0.4987   0.01194   0.00631  -0.0319   0.9229   0.0300
  -6.000  -0.4741   0.01150   0.00583  -0.0312   0.9109   0.0306
  -5.750  -0.4489   0.01116   0.00544  -0.0306   0.8996   0.0311
  -5.250  -0.3974   0.01058   0.00475  -0.0297   0.8768   0.0322
  -5.000  -0.3711   0.01033   0.00444  -0.0293   0.8658   0.0328
  -4.500  -0.3179   0.00989   0.00389  -0.0287   0.8433   0.0341
  -4.250  -0.2908   0.00973   0.00368  -0.0285   0.8324   0.0346
  -3.750  -0.2375   0.00921   0.00306  -0.0279   0.8095   0.0370
  -3.500  -0.2102   0.00904   0.00285  -0.0277   0.7985   0.0385
  -3.000  -0.1553   0.00876   0.00249  -0.0274   0.7760   0.0419
  -2.750  -0.1281   0.00857   0.00231  -0.0273   0.7652   0.0479
  -2.500  -0.1018   0.00827   0.00210  -0.0270   0.7542   0.0758
  -2.250  -0.0711   0.00861   0.00260  -0.0274   0.7432   0.1154
  -2.000  -0.0408   0.00892   0.00285  -0.0277   0.7326   0.1215
  -1.750  -0.0115   0.00909   0.00296  -0.0279   0.7214   0.1242
  -1.500   0.0173   0.00915   0.00300  -0.0280   0.7107   0.1270
  -1.250   0.0461   0.00926   0.00306  -0.0281   0.6999   0.1300
  -1.000   0.0748   0.00936   0.00311  -0.0282   0.6885   0.1328
  -0.750   0.1040   0.00959   0.00326  -0.0284   0.6771   0.1345
  -0.500   0.1307   0.00923   0.00293  -0.0282   0.6659   0.1375
  -0.250   0.1585   0.00918   0.00285  -0.0282   0.6538   0.1397
   0.000   0.1866   0.00913   0.00279  -0.0283   0.6415   0.1413
   0.250   0.2149   0.00919   0.00280  -0.0284   0.6291   0.1438
   0.500   0.2437   0.00937   0.00291  -0.0285   0.6162   0.1457
   0.750   0.2708   0.00922   0.00274  -0.0284   0.6031   0.1460
   1.000   0.2984   0.00911   0.00263  -0.0284   0.5898   0.1463
   1.250   0.3255   0.00895   0.00247  -0.0283   0.5767   0.1473
   1.500   0.3529   0.00891   0.00241  -0.0282   0.5622   0.1478
   1.750   0.3805   0.00893   0.00239  -0.0282   0.5462   0.1475
   2.000   0.4081   0.00895   0.00238  -0.0282   0.5317   0.1473
   2.250   0.4357   0.00898   0.00237  -0.0282   0.5192   0.1470
   2.500   0.4635   0.00900   0.00238  -0.0282   0.5068   0.1468
   2.750   0.4913   0.00902   0.00240  -0.0282   0.4948   0.1466
   3.000   0.5189   0.00906   0.00242  -0.0282   0.4834   0.1464
   3.500   0.5741   0.00913   0.00247  -0.0282   0.4589   0.1462
   3.750   0.6015   0.00918   0.00250  -0.0282   0.4450   0.1462
   4.000   0.6281   0.00928   0.00253  -0.0281   0.4224   0.1466
   4.250   0.6549   0.00937   0.00257  -0.0280   0.4010   0.1469
   4.500   0.6817   0.00949   0.00264  -0.0279   0.3804   0.1470
   4.750   0.7085   0.00960   0.00273  -0.0278   0.3623   0.1472
   5.000   0.7349   0.00976   0.00282  -0.0276   0.3418   0.1475
   5.250   0.7612   0.00993   0.00293  -0.0275   0.3201   0.1479
   5.500   0.7872   0.01013   0.00307  -0.0273   0.2966   0.1485
   5.750   0.8127   0.01038   0.00324  -0.0270   0.2711   0.1492
   6.000   0.8376   0.01070   0.00344  -0.0266   0.2410   0.1499
   6.250   0.8619   0.01107   0.00368  -0.0262   0.2095   0.1507
   6.500   0.8861   0.01146   0.00395  -0.0258   0.1814   0.1515
   6.750   0.9099   0.01186   0.00424  -0.0253   0.1548   0.1524
   7.000   0.9333   0.01229   0.00455  -0.0248   0.1273   0.1532
   7.250   0.9554   0.01285   0.00494  -0.0240   0.0951   0.1539
   7.500   0.9771   0.01343   0.00537  -0.0232   0.0689   0.1546
   7.750   1.0001   0.01387   0.00576  -0.0226   0.0569   0.1552
   8.000   1.0236   0.01425   0.00612  -0.0220   0.0503   0.1558
   8.250   1.0469   0.01462   0.00650  -0.0214   0.0459   0.1566
   8.500   1.0702   0.01499   0.00688  -0.0208   0.0427   0.1578
   8.750   1.0940   0.01529   0.00721  -0.0203   0.0405   0.1594
   9.000   1.1164   0.01569   0.00762  -0.0196   0.0379   0.1612
   9.250   1.1382   0.01613   0.00810  -0.0188   0.0359   0.1634
   9.500   1.1613   0.01643   0.00846  -0.0182   0.0346   0.1666
   9.750   1.1833   0.01671   0.00890  -0.0176   0.0330   0.2699
  10.000   1.2034   0.01716   0.00944  -0.0166   0.0312   0.3130
  10.250   1.2215   0.01629   0.01017  -0.0153   0.0298   0.9935
  10.500   1.2451   0.01668   0.01060  -0.0150   0.0287   1.0000
  10.750   1.2648   0.01711   0.01105  -0.0140   0.0276   1.0000
  11.000   1.2826   0.01764   0.01159  -0.0126   0.0264   1.0000
  11.250   1.2942   0.01844   0.01242  -0.0103   0.0249   1.0000
  11.500   1.3117   0.01882   0.01284  -0.0089   0.0242   1.0000
  11.750   1.3274   0.01932   0.01338  -0.0072   0.0233   1.0000
  12.000   1.3424   0.01989   0.01398  -0.0056   0.0224   1.0000
  12.250   1.3551   0.02064   0.01475  -0.0039   0.0215   1.0000
  12.500   1.3615   0.02182   0.01599  -0.0015   0.0205   1.0000
  12.750   1.3767   0.02250   0.01672  -0.0003   0.0201   1.0000
  13.000   1.3902   0.02332   0.01760   0.0009   0.0194   1.0000
  13.250   1.4031   0.02422   0.01854   0.0021   0.0188   1.0000
  13.500   1.4150   0.02523   0.01960   0.0032   0.0181   1.0000
  13.750   1.4235   0.02655   0.02095   0.0044   0.0175   1.0000
  14.000   1.4252   0.02849   0.02297   0.0059   0.0168   1.0000
  14.250   1.4364   0.02974   0.02430   0.0066   0.0165   1.0000
  14.500   1.4454   0.03121   0.02584   0.0073   0.0161   1.0000
  14.750   1.4532   0.03285   0.02755   0.0079   0.0156   1.0000
  15.000   1.4600   0.03465   0.02941   0.0083   0.0153   1.0000
  15.250   1.4656   0.03660   0.03145   0.0087   0.0149   1.0000
  15.500   1.4690   0.03885   0.03376   0.0090   0.0146   1.0000
  15.750   1.4689   0.04155   0.03653   0.0091   0.0142   1.0000
  16.000   1.4631   0.04495   0.04002   0.0090   0.0139   1.0000
  16.250   1.4531   0.04897   0.04415   0.0087   0.0136   1.0000
  16.500   1.4541   0.05183   0.04711   0.0083   0.0135   1.0000
  16.750   1.4531   0.05500   0.05038   0.0077   0.0133   1.0000
  17.000   1.4504   0.05849   0.05398   0.0069   0.0131   1.0000
  17.250   1.4466   0.06222   0.05781   0.0059   0.0129   1.0000
  17.500   1.4416   0.06616   0.06185   0.0048   0.0127   1.0000
  17.750   1.4354   0.07036   0.06614   0.0036   0.0126   1.0000
  18.000   1.4282   0.07480   0.07069   0.0021   0.0124   1.0000
  18.250   1.4202   0.07943   0.07541   0.0005   0.0122   1.0000
  18.500   1.4109   0.08429   0.08038  -0.0013   0.0121   1.0000
  18.750   1.4000   0.08951   0.08569  -0.0032   0.0119   1.0000
  19.000   1.3886   0.09490   0.09119  -0.0054   0.0118   1.0000
  19.250   1.3762   0.10049   0.09687  -0.0077   0.0117   1.0000
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