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NACA M2 (nacam2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M2 (nacam2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 60.31 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacam2-il-1000000.txt
Download as CSV file: xf-nacam2-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M2                                         
  
 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  -0.8628   0.09065   0.08906  -0.0008   1.0000   0.0087
 -14.000  -0.8415   0.09146   0.08990  -0.0002   1.0000   0.0089
 -13.750  -1.0758   0.07369   0.07197   0.0009   1.0000   0.0078
 -13.500  -1.1449   0.05148   0.04936  -0.0186   1.0000   0.0075
 -13.250  -1.1721   0.04449   0.04212  -0.0225   1.0000   0.0075
 -13.000  -1.1915   0.04013   0.03753  -0.0222   1.0000   0.0075
 -12.750  -1.2045   0.03713   0.03431  -0.0197   1.0000   0.0076
 -12.500  -1.2093   0.03448   0.03144  -0.0172   1.0000   0.0077
 -12.250  -1.2050   0.03221   0.02895  -0.0154   1.0000   0.0078
 -12.000  -1.1953   0.03037   0.02690  -0.0140   1.0000   0.0079
 -11.750  -1.1815   0.02890   0.02526  -0.0128   1.0000   0.0080
 -11.500  -1.1821   0.02506   0.02096  -0.0103   1.0000   0.0084
 -11.250  -1.1678   0.02331   0.01902  -0.0090   1.0000   0.0087
 -11.000  -1.1472   0.02247   0.01809  -0.0083   1.0000   0.0091
 -10.750  -1.1248   0.02189   0.01746  -0.0078   1.0000   0.0094
 -10.500  -1.1021   0.02131   0.01680  -0.0073   1.0000   0.0098
 -10.250  -1.0797   0.02060   0.01599  -0.0068   1.0000   0.0102
 -10.000  -1.0574   0.01980   0.01507  -0.0062   1.0000   0.0106
  -9.750  -1.0345   0.01908   0.01423  -0.0057   1.0000   0.0109
  -9.500  -1.0150   0.01758   0.01253  -0.0046   1.0000   0.0114
  -9.250  -0.9925   0.01672   0.01160  -0.0041   1.0000   0.0122
  -9.000  -0.9672   0.01640   0.01125  -0.0038   1.0000   0.0127
  -8.750  -0.9418   0.01606   0.01087  -0.0036   1.0000   0.0133
  -8.500  -0.9166   0.01563   0.01039  -0.0032   1.0000   0.0140
  -8.250  -0.8910   0.01528   0.00997  -0.0030   1.0000   0.0146
  -8.000  -0.8678   0.01439   0.00898  -0.0024   1.0000   0.0156
  -7.750  -0.8419   0.01411   0.00870  -0.0022   1.0000   0.0165
  -7.500  -0.8155   0.01393   0.00852  -0.0020   1.0000   0.0174
  -7.250  -0.7894   0.01366   0.00822  -0.0018   1.0000   0.0184
  -7.000  -0.7631   0.01342   0.00794  -0.0016   1.0000   0.0192
  -6.750  -0.7362   0.01334   0.00782  -0.0014   1.0000   0.0198
  -6.500  -0.7139   0.01218   0.00661  -0.0007   1.0000   0.0216
  -6.250  -0.6878   0.01196   0.00639  -0.0004   1.0000   0.0228
  -6.000  -0.6619   0.01167   0.00609  -0.0001   1.0000   0.0240
  -5.750  -0.6363   0.01137   0.00576   0.0003   1.0000   0.0251
  -5.500  -0.6105   0.01117   0.00554   0.0007   1.0000   0.0260
  -5.250  -0.5849   0.01100   0.00535   0.0011   1.0000   0.0266
  -5.000  -0.5630   0.01004   0.00431   0.0021   1.0000   0.0287
  -4.750  -0.5388   0.00967   0.00393   0.0028   1.0000   0.0300
  -4.500  -0.5144   0.00941   0.00366   0.0035   1.0000   0.0315
  -4.250  -0.4903   0.00916   0.00339   0.0042   1.0000   0.0327
  -4.000  -0.4663   0.00893   0.00314   0.0050   1.0000   0.0337
  -3.750  -0.4425   0.00874   0.00293   0.0058   1.0000   0.0346
  -3.500  -0.4188   0.00858   0.00277   0.0066   1.0000   0.0351
  -3.250  -0.3906   0.00830   0.00244   0.0065   0.9993   0.0370
  -3.000  -0.3559   0.00803   0.00219   0.0049   0.9975   0.0409
  -2.750  -0.3208   0.00782   0.00199   0.0033   0.9957   0.0454
  -2.500  -0.2863   0.00730   0.00177   0.0015   0.9942   0.1111
  -2.250  -0.2542   0.00664   0.00157   0.0002   0.9911   0.2229
  -2.000  -0.2203   0.00606   0.00141  -0.0015   0.9880   0.3344
  -1.750  -0.1853   0.00548   0.00127  -0.0034   0.9839   0.4546
  -1.500  -0.1545   0.00510   0.00119  -0.0042   0.9752   0.5375
  -1.250  -0.1244   0.00482   0.00113  -0.0047   0.9668   0.6054
  -1.000  -0.0972   0.00455   0.00110  -0.0045   0.9560   0.6731
  -0.750  -0.0717   0.00434   0.00108  -0.0037   0.9426   0.7315
  -0.500  -0.0471   0.00415   0.00108  -0.0027   0.9277   0.7901
  -0.250  -0.0231   0.00404   0.00108  -0.0015   0.9056   0.8341
   0.000   0.0000   0.00402   0.00106   0.0000   0.8702   0.8702
   0.250   0.0231   0.00404   0.00108   0.0015   0.8348   0.9062
   0.500   0.0471   0.00415   0.00108   0.0027   0.7901   0.9278
   0.750   0.0718   0.00434   0.00108   0.0037   0.7323   0.9425
   1.000   0.0972   0.00455   0.00110   0.0045   0.6737   0.9559
   1.250   0.1244   0.00482   0.00113   0.0047   0.6057   0.9668
   1.500   0.1545   0.00510   0.00119   0.0042   0.5384   0.9752
   1.750   0.1853   0.00548   0.00127   0.0034   0.4556   0.9839
   2.000   0.2203   0.00606   0.00141   0.0015   0.3346   0.9880
   2.250   0.2542   0.00665   0.00157  -0.0002   0.2225   0.9911
   2.500   0.2863   0.00729   0.00177  -0.0015   0.1122   0.9942
   2.750   0.3208   0.00782   0.00199  -0.0033   0.0454   0.9957
   3.000   0.3559   0.00803   0.00218  -0.0049   0.0409   0.9976
   3.250   0.3906   0.00829   0.00244  -0.0065   0.0371   0.9994
   3.500   0.4187   0.00858   0.00277  -0.0066   0.0351   1.0000
   3.750   0.4424   0.00874   0.00293  -0.0058   0.0346   1.0000
   4.000   0.4662   0.00893   0.00314  -0.0050   0.0337   1.0000
   4.250   0.4902   0.00916   0.00339  -0.0042   0.0327   1.0000
   4.500   0.5144   0.00941   0.00366  -0.0035   0.0315   1.0000
   4.750   0.5387   0.00967   0.00393  -0.0028   0.0300   1.0000
   5.000   0.5630   0.01004   0.00431  -0.0021   0.0287   1.0000
   5.250   0.5849   0.01100   0.00535  -0.0011   0.0266   1.0000
   5.500   0.6104   0.01117   0.00554  -0.0006   0.0260   1.0000
   5.750   0.6363   0.01137   0.00576  -0.0003   0.0251   1.0000
   6.000   0.6619   0.01166   0.00608   0.0001   0.0240   1.0000
   6.250   0.6878   0.01195   0.00639   0.0004   0.0228   1.0000
   6.500   0.7139   0.01219   0.00661   0.0007   0.0216   1.0000
   6.750   0.7362   0.01334   0.00782   0.0014   0.0198   1.0000
   7.000   0.7631   0.01341   0.00793   0.0016   0.0192   1.0000
   7.250   0.7894   0.01365   0.00822   0.0018   0.0183   1.0000
   7.500   0.8155   0.01393   0.00852   0.0020   0.0174   1.0000
   7.750   0.8420   0.01410   0.00870   0.0022   0.0165   1.0000
   8.000   0.8678   0.01439   0.00899   0.0024   0.0156   1.0000
   8.250   0.8910   0.01529   0.00998   0.0030   0.0146   1.0000
   8.500   0.9166   0.01563   0.01039   0.0032   0.0140   1.0000
   8.750   0.9418   0.01605   0.01087   0.0035   0.0133   1.0000
   9.000   0.9672   0.01640   0.01125   0.0038   0.0127   1.0000
   9.250   0.9926   0.01671   0.01159   0.0040   0.0121   1.0000
   9.500   1.0151   0.01760   0.01254   0.0046   0.0114   1.0000
   9.750   1.0345   0.01910   0.01425   0.0056   0.0109   1.0000
  10.000   1.0575   0.01981   0.01508   0.0062   0.0106   1.0000
  10.250   1.0799   0.02060   0.01599   0.0068   0.0102   1.0000
  10.500   1.1024   0.02130   0.01678   0.0073   0.0098   1.0000
  10.750   1.1251   0.02187   0.01744   0.0078   0.0094   1.0000
  11.000   1.1474   0.02246   0.01809   0.0083   0.0091   1.0000
  11.250   1.1679   0.02332   0.01903   0.0089   0.0087   1.0000
  11.500   1.1823   0.02507   0.02096   0.0102   0.0084   1.0000
  11.750   1.1820   0.02888   0.02524   0.0127   0.0080   1.0000
  12.000   1.1959   0.03034   0.02687   0.0139   0.0079   1.0000
  12.250   1.2054   0.03221   0.02895   0.0153   0.0078   1.0000
  12.500   1.2099   0.03447   0.03143   0.0171   0.0076   1.0000
  12.750   1.2054   0.03711   0.03429   0.0195   0.0075   1.0000
  13.000   1.1919   0.04019   0.03759   0.0221   0.0075   1.0000
  13.250   1.1735   0.04443   0.04206   0.0224   0.0074   1.0000
  13.500   1.1460   0.05149   0.04937   0.0184   0.0075   1.0000
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