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NACA M2 (nacam2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M2 (nacam2-il)
Reynolds number: 100,000
Max Cl/Cd: 27.94 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam2-il-100000-n5.txt
Download as CSV file: xf-nacam2-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7428   0.08759   0.08262  -0.0024   1.0000   0.0281
 -10.000  -0.7570   0.07863   0.07368  -0.0098   1.0000   0.0278
  -9.750  -0.7751   0.07182   0.06678  -0.0149   1.0000   0.0275
  -9.500  -0.7944   0.06658   0.06141  -0.0163   1.0000   0.0274
  -9.250  -0.8094   0.06133   0.05592  -0.0166   1.0000   0.0274
  -9.000  -0.8194   0.05608   0.05032  -0.0163   1.0000   0.0275
  -8.750  -0.8241   0.05103   0.04480  -0.0154   1.0000   0.0278
  -8.500  -0.8227   0.04647   0.03967  -0.0141   1.0000   0.0283
  -8.250  -0.8168   0.04224   0.03506  -0.0130   1.0000   0.0294
  -8.000  -0.8022   0.04015   0.03279  -0.0123   1.0000   0.0312
  -7.750  -0.7862   0.03788   0.03024  -0.0114   1.0000   0.0332
  -7.500  -0.7702   0.03485   0.02672  -0.0102   1.0000   0.0349
  -7.250  -0.7515   0.03223   0.02356  -0.0091   1.0000   0.0372
  -7.000  -0.7311   0.02996   0.02081  -0.0081   1.0000   0.0398
  -6.750  -0.7096   0.02791   0.01863  -0.0074   1.0000   0.0421
  -6.500  -0.6867   0.02649   0.01702  -0.0068   1.0000   0.0450
  -6.250  -0.6629   0.02519   0.01543  -0.0061   1.0000   0.0487
  -6.000  -0.6384   0.02384   0.01383  -0.0054   1.0000   0.0506
  -5.750  -0.6153   0.02238   0.01235  -0.0047   1.0000   0.0536
  -5.500  -0.5917   0.02144   0.01138  -0.0041   1.0000   0.0574
  -5.250  -0.5680   0.02044   0.01029  -0.0033   1.0000   0.0600
  -5.000  -0.5446   0.01955   0.00926  -0.0025   1.0000   0.0624
  -4.750  -0.5217   0.01867   0.00834  -0.0016   1.0000   0.0652
  -4.500  -0.4988   0.01791   0.00756  -0.0008   1.0000   0.0693
  -4.250  -0.4751   0.01731   0.00687   0.0000   1.0000   0.0762
  -4.000  -0.4520   0.01661   0.00621   0.0008   1.0000   0.0881
  -3.750  -0.4292   0.01583   0.00558   0.0016   1.0000   0.1113
  -3.500  -0.4072   0.01491   0.00503   0.0024   1.0000   0.1798
  -3.250  -0.3859   0.01398   0.00463   0.0032   1.0000   0.2923
  -3.000  -0.3649   0.01318   0.00433   0.0042   1.0000   0.4072
  -2.750  -0.3449   0.01243   0.00420   0.0058   1.0000   0.5439
  -2.500  -0.3249   0.01189   0.00424   0.0081   1.0000   0.6781
  -2.250  -0.3038   0.01168   0.00441   0.0108   1.0000   0.7887
  -2.000  -0.2769   0.01172   0.00457   0.0123   1.0000   0.8632
  -1.750  -0.2413   0.01184   0.00466   0.0116   1.0000   0.9092
  -1.500  -0.2011   0.01192   0.00464   0.0094   1.0000   0.9386
  -1.250  -0.1600   0.01196   0.00458   0.0067   1.0000   0.9587
  -1.000  -0.1163   0.01198   0.00450   0.0032   1.0000   0.9755
  -0.750  -0.0672   0.01196   0.00442  -0.0014   1.0000   0.9892
  -0.500  -0.0245   0.01191   0.00433  -0.0050   1.0000   1.0000
  -0.250  -0.0121   0.01184   0.00425  -0.0025   1.0000   1.0000
   0.000   0.0000   0.01181   0.00423   0.0000   1.0000   1.0000
   0.250   0.0121   0.01184   0.00425   0.0025   1.0000   1.0000
   0.500   0.0245   0.01191   0.00433   0.0050   1.0000   1.0000
   0.750   0.0672   0.01196   0.00442   0.0014   0.9892   1.0000
   1.000   0.1162   0.01198   0.00450  -0.0032   0.9755   1.0000
   1.250   0.1600   0.01196   0.00458  -0.0067   0.9587   1.0000
   1.500   0.2011   0.01192   0.00464  -0.0094   0.9386   1.0000
   1.750   0.2413   0.01184   0.00466  -0.0116   0.9092   1.0000
   2.000   0.2769   0.01172   0.00457  -0.0123   0.8631   1.0000
   2.250   0.3038   0.01168   0.00441  -0.0108   0.7889   1.0000
   2.500   0.3248   0.01189   0.00424  -0.0081   0.6782   1.0000
   2.750   0.3448   0.01243   0.00420  -0.0058   0.5441   1.0000
   3.000   0.3648   0.01318   0.00433  -0.0042   0.4075   1.0000
   3.500   0.4072   0.01490   0.00503  -0.0024   0.1800   1.0000
   3.750   0.4291   0.01583   0.00558  -0.0016   0.1114   1.0000
   4.000   0.4520   0.01661   0.00621  -0.0008   0.0881   1.0000
   4.250   0.4751   0.01731   0.00687   0.0000   0.0762   1.0000
   4.500   0.4988   0.01791   0.00756   0.0008   0.0693   1.0000
   4.750   0.5217   0.01867   0.00834   0.0016   0.0652   1.0000
   5.000   0.5445   0.01954   0.00926   0.0025   0.0624   1.0000
   5.250   0.5680   0.02044   0.01029   0.0033   0.0600   1.0000
   5.500   0.5917   0.02143   0.01138   0.0041   0.0574   1.0000
   5.750   0.6153   0.02238   0.01235   0.0047   0.0536   1.0000
   6.000   0.6384   0.02384   0.01382   0.0054   0.0506   1.0000
   6.250   0.6629   0.02519   0.01543   0.0061   0.0487   1.0000
   6.500   0.6867   0.02649   0.01702   0.0068   0.0450   1.0000
   6.750   0.7096   0.02791   0.01863   0.0074   0.0421   1.0000
   7.000   0.7311   0.02996   0.02081   0.0081   0.0398   1.0000
   7.250   0.7515   0.03222   0.02356   0.0091   0.0372   1.0000
   7.500   0.7702   0.03485   0.02672   0.0102   0.0349   1.0000
   7.750   0.7863   0.03788   0.03024   0.0114   0.0332   1.0000
   8.000   0.8022   0.04015   0.03279   0.0123   0.0312   1.0000
   8.250   0.8169   0.04224   0.03506   0.0130   0.0294   1.0000
   8.500   0.8228   0.04647   0.03967   0.0141   0.0283   1.0000
   8.750   0.8241   0.05103   0.04481   0.0154   0.0278   1.0000
   9.000   0.8195   0.05609   0.05034   0.0163   0.0275   1.0000
   9.250   0.8095   0.06136   0.05594   0.0166   0.0274   1.0000
   9.500   0.7945   0.06662   0.06144   0.0162   0.0274   1.0000
   9.750   0.7754   0.07186   0.06682   0.0148   0.0275   1.0000
  10.000   0.7573   0.07871   0.07377   0.0097   0.0278   1.0000
  10.250   0.7432   0.08771   0.08273   0.0022   0.0281   1.0000
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