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NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 747A415 (naca747a415-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.88 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca747a415-il-1000000-n5.txt
Download as CSV file: xf-naca747a415-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 747A415                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -1.0405   0.06637   0.06372  -0.0561   1.0000   0.0102
 -17.250  -1.0794   0.05542   0.05253  -0.0640   1.0000   0.0102
 -17.000  -1.0983   0.04936   0.04631  -0.0676   1.0000   0.0102
 -16.750  -1.1166   0.04436   0.04113  -0.0695   1.0000   0.0102
 -16.500  -1.1260   0.04091   0.03755  -0.0700   1.0000   0.0102
 -16.250  -1.1298   0.03828   0.03479  -0.0698   1.0000   0.0103
 -16.000  -1.1295   0.03617   0.03257  -0.0693   1.0000   0.0104
 -15.750  -1.1295   0.03416   0.03045  -0.0684   1.0000   0.0104
 -15.500  -1.1285   0.03234   0.02852  -0.0672   1.0000   0.0105
 -15.000  -1.1086   0.02876   0.02467  -0.0679   0.9365   0.0108
 -14.750  -1.1023   0.02772   0.02344  -0.0660   0.9027   0.0109
 -14.500  -1.0962   0.02677   0.02235  -0.0639   0.8789   0.0110
 -14.250  -1.0879   0.02593   0.02136  -0.0619   0.8587   0.0111
 -14.000  -1.0775   0.02519   0.02051  -0.0600   0.8416   0.0113
 -13.750  -1.0672   0.02442   0.01962  -0.0581   0.8255   0.0115
 -13.500  -1.0549   0.02377   0.01886  -0.0564   0.8103   0.0116
 -13.250  -1.0442   0.02299   0.01795  -0.0544   0.7962   0.0118
 -13.000  -1.0291   0.02251   0.01737  -0.0528   0.7830   0.0120
 -12.750  -1.0174   0.02178   0.01651  -0.0507   0.7709   0.0122
 -12.500  -1.0031   0.02122   0.01585  -0.0489   0.7605   0.0124
 -12.250  -0.9888   0.02067   0.01518  -0.0470   0.7509   0.0125
 -12.000  -0.9734   0.02011   0.01451  -0.0453   0.7420   0.0127
 -11.750  -0.9550   0.01959   0.01389  -0.0440   0.7341   0.0128
 -11.500  -0.9357   0.01907   0.01327  -0.0429   0.7263   0.0130
 -11.250  -0.9174   0.01844   0.01253  -0.0417   0.7187   0.0132
 -11.000  -0.8978   0.01786   0.01188  -0.0406   0.7120   0.0134
 -10.750  -0.8767   0.01740   0.01135  -0.0397   0.7052   0.0137
 -10.500  -0.8549   0.01696   0.01085  -0.0390   0.6992   0.0139
 -10.250  -0.8321   0.01658   0.01043  -0.0383   0.6932   0.0142
 -10.000  -0.8091   0.01622   0.01000  -0.0377   0.6871   0.0145
  -9.750  -0.7858   0.01586   0.00958  -0.0371   0.6817   0.0148
  -9.500  -0.7623   0.01548   0.00913  -0.0365   0.6758   0.0151
  -9.250  -0.7387   0.01512   0.00870  -0.0360   0.6698   0.0154
  -9.000  -0.7148   0.01475   0.00826  -0.0354   0.6645   0.0156
  -8.750  -0.6905   0.01442   0.00786  -0.0350   0.6586   0.0158
  -8.500  -0.6667   0.01403   0.00741  -0.0344   0.6526   0.0161
  -8.250  -0.6427   0.01362   0.00696  -0.0339   0.6475   0.0165
  -8.000  -0.6179   0.01331   0.00661  -0.0335   0.6418   0.0169
  -7.750  -0.5928   0.01304   0.00630  -0.0331   0.6361   0.0173
  -7.500  -0.5673   0.01278   0.00601  -0.0328   0.6312   0.0177
  -7.250  -0.5418   0.01252   0.00570  -0.0325   0.6256   0.0182
  -7.000  -0.5162   0.01227   0.00539  -0.0322   0.6199   0.0186
  -6.750  -0.4904   0.01203   0.00511  -0.0320   0.6152   0.0189
  -6.500  -0.4644   0.01180   0.00484  -0.0317   0.6097   0.0193
  -6.250  -0.4389   0.01152   0.00452  -0.0314   0.6045   0.0199
  -6.000  -0.4127   0.01130   0.00429  -0.0312   0.6000   0.0207
  -5.750  -0.3862   0.01110   0.00407  -0.0310   0.5957   0.0214
  -5.500  -0.3596   0.01092   0.00386  -0.0309   0.5909   0.0222
  -5.250  -0.3329   0.01076   0.00365  -0.0308   0.5863   0.0228
  -5.000  -0.3064   0.01055   0.00343  -0.0306   0.5825   0.0239
  -4.750  -0.2796   0.01038   0.00326  -0.0305   0.5783   0.0251
  -4.500  -0.2526   0.01023   0.00309  -0.0304   0.5740   0.0265
  -4.250  -0.2256   0.01010   0.00292  -0.0303   0.5698   0.0279
  -4.000  -0.1986   0.00994   0.00278  -0.0303   0.5663   0.0303
  -3.750  -0.1712   0.00981   0.00264  -0.0303   0.5627   0.0327
  -3.500  -0.1440   0.00967   0.00251  -0.0302   0.5588   0.0362
  -3.250  -0.1167   0.00956   0.00239  -0.0302   0.5551   0.0400
  -3.000  -0.0893   0.00945   0.00228  -0.0302   0.5518   0.0449
  -2.750  -0.0618   0.00932   0.00218  -0.0303   0.5489   0.0516
  -2.500  -0.0344   0.00919   0.00209  -0.0303   0.5458   0.0602
  -2.250  -0.0070   0.00906   0.00199  -0.0303   0.5427   0.0728
  -2.000   0.0199   0.00890   0.00191  -0.0303   0.5396   0.0950
  -1.500   0.0719   0.00835   0.00172  -0.0300   0.5342   0.2061
  -1.250   0.0967   0.00794   0.00162  -0.0298   0.5316   0.2993
  -1.000   0.1213   0.00751   0.00152  -0.0295   0.5291   0.4018
  -0.750   0.1457   0.00707   0.00142  -0.0292   0.5267   0.5066
  -0.500   0.1662   0.00632   0.00131  -0.0281   0.5245   0.6910
  -0.250   0.1921   0.00623   0.00142  -0.0277   0.5222   0.7646
   0.000   0.2202   0.00629   0.00150  -0.0277   0.5200   0.7887
   0.250   0.2485   0.00636   0.00158  -0.0277   0.5185   0.8047
   0.500   0.2769   0.00639   0.00165  -0.0278   0.5168   0.8123
   0.750   0.3059   0.00644   0.00169  -0.0281   0.5151   0.8170
   1.000   0.3350   0.00649   0.00171  -0.0284   0.5133   0.8197
   1.250   0.3641   0.00653   0.00174  -0.0288   0.5115   0.8219
   1.500   0.3929   0.00657   0.00178  -0.0290   0.5098   0.8244
   1.750   0.4216   0.00661   0.00182  -0.0293   0.5081   0.8264
   2.000   0.4504   0.00667   0.00186  -0.0296   0.5062   0.8279
   2.250   0.4791   0.00673   0.00191  -0.0299   0.5042   0.8292
   2.500   0.5082   0.00677   0.00196  -0.0303   0.5030   0.8305
   2.750   0.5373   0.00680   0.00201  -0.0307   0.5013   0.8320
   3.000   0.5663   0.00684   0.00206  -0.0311   0.4988   0.8334
   3.250   0.5951   0.00690   0.00211  -0.0314   0.4958   0.8346
   3.500   0.6238   0.00696   0.00217  -0.0317   0.4929   0.8359
   3.750   0.6523   0.00703   0.00224  -0.0320   0.4902   0.8370
   4.000   0.6809   0.00710   0.00231  -0.0324   0.4867   0.8381
   4.250   0.7096   0.00714   0.00237  -0.0327   0.4816   0.8393
   4.500   0.7375   0.00722   0.00244  -0.0329   0.4748   0.8407
   4.750   0.7655   0.00728   0.00252  -0.0331   0.4661   0.8421
   5.000   0.7927   0.00740   0.00262  -0.0332   0.4560   0.8437
   5.250   0.8206   0.00748   0.00271  -0.0335   0.4454   0.8453
   5.500   0.8471   0.00764   0.00283  -0.0335   0.4263   0.8469
   5.750   0.8700   0.00805   0.00305  -0.0329   0.3813   0.8486
   6.000   0.8885   0.00875   0.00349  -0.0318   0.3269   0.8505
   6.250   0.9047   0.00957   0.00402  -0.0303   0.2690   0.8526
   6.500   0.9178   0.01049   0.00463  -0.0284   0.2076   0.8548
   6.750   0.9317   0.01125   0.00517  -0.0265   0.1626   0.8569
   7.000   0.9422   0.01206   0.00576  -0.0241   0.1182   0.8596
   7.250   0.9528   0.01277   0.00632  -0.0216   0.0878   0.8624
   7.500   0.9640   0.01326   0.00677  -0.0192   0.0725   0.8655
   7.750   0.9735   0.01375   0.00723  -0.0164   0.0616   0.8690
   8.000   0.9800   0.01444   0.00785  -0.0134   0.0475   0.8726
   8.250   0.9877   0.01512   0.00851  -0.0108   0.0376   0.8766
   8.500   0.9975   0.01580   0.00919  -0.0086   0.0314   0.8806
   8.750   1.0087   0.01649   0.00990  -0.0068   0.0278   0.8848
   9.000   1.0214   0.01716   0.01058  -0.0053   0.0256   0.8887
   9.250   1.0328   0.01789   0.01135  -0.0037   0.0238   0.8930
   9.500   1.0443   0.01866   0.01216  -0.0022   0.0223   0.8981
   9.750   1.0568   0.01944   0.01298  -0.0009   0.0209   0.9034
  10.000   1.0673   0.02033   0.01391   0.0006   0.0193   0.9091
  10.250   1.0782   0.02123   0.01486   0.0019   0.0181   0.9161
  10.500   1.0898   0.02212   0.01580   0.0031   0.0173   0.9238
  10.750   1.1006   0.02308   0.01682   0.0043   0.0165   0.9343
  11.000   1.1134   0.02413   0.01794   0.0048   0.0155   0.9493
  11.250   1.1377   0.02530   0.01918   0.0028   0.0141   0.9660
  11.500   1.1578   0.02652   0.02044   0.0016   0.0132   1.0000
  11.750   1.1676   0.02781   0.02175   0.0023   0.0125   1.0000
  12.000   1.1778   0.02910   0.02306   0.0030   0.0121   1.0000
  12.250   1.1881   0.03039   0.02439   0.0036   0.0116   1.0000
  12.500   1.1977   0.03174   0.02578   0.0042   0.0113   1.0000
  12.750   1.2067   0.03316   0.02724   0.0048   0.0109   1.0000
  13.000   1.2153   0.03466   0.02877   0.0053   0.0104   1.0000
  13.250   1.2236   0.03623   0.03037   0.0058   0.0101   1.0000
  13.500   1.2309   0.03790   0.03208   0.0063   0.0099   1.0000
  13.750   1.2392   0.03952   0.03374   0.0067   0.0096   1.0000
  14.000   1.2474   0.04120   0.03547   0.0070   0.0095   1.0000
  14.250   1.2557   0.04288   0.03720   0.0072   0.0092   1.0000
  14.500   1.2631   0.04468   0.03906   0.0074   0.0091   1.0000
  14.750   1.2706   0.04649   0.04091   0.0076   0.0089   1.0000
  15.000   1.2766   0.04851   0.04299   0.0077   0.0089   1.0000
  15.250   1.2833   0.05047   0.04500   0.0078   0.0087   1.0000
  15.500   1.2888   0.05259   0.04718   0.0078   0.0087   1.0000
  15.750   1.2948   0.05469   0.04933   0.0078   0.0085   1.0000
  16.000   1.3000   0.05692   0.05163   0.0076   0.0084   1.0000
  16.250   1.3050   0.05920   0.05395   0.0074   0.0082   1.0000
  16.500   1.3092   0.06163   0.05644   0.0072   0.0081   1.0000
  16.750   1.3120   0.06422   0.05910   0.0069   0.0081   1.0000
  17.000   1.3156   0.06680   0.06173   0.0065   0.0080   1.0000
  17.250   1.3179   0.06956   0.06456   0.0060   0.0080   1.0000
  17.500   1.3188   0.07256   0.06763   0.0054   0.0078   1.0000
  17.750   1.3176   0.07587   0.07102   0.0047   0.0077   1.0000
  18.000   1.3167   0.07920   0.07443   0.0039   0.0076   1.0000
  18.250   1.3168   0.08250   0.07781   0.0030   0.0076   1.0000
  18.500   1.3180   0.08568   0.08106   0.0020   0.0076   1.0000
  18.750   1.3156   0.08943   0.08490   0.0008   0.0075   1.0000
  19.000   1.3140   0.09312   0.08867  -0.0004   0.0075   1.0000
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