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NACA-M1 AIRFOIL (m1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA-M1 AIRFOIL (m1-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.36 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m1-il-1000000-n5.txt
Download as CSV file: xf-m1-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA-M1 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7560   0.12933   0.12775   0.0395   1.0000   0.0027
 -11.250  -0.7594   0.12348   0.12191   0.0372   1.0000   0.0028
 -10.750  -1.0826   0.03428   0.03166  -0.0077   1.0000   0.0022
 -10.500  -1.0800   0.02911   0.02601  -0.0066   1.0000   0.0023
 -10.250  -1.0668   0.02617   0.02274  -0.0057   1.0000   0.0023
 -10.000  -1.0492   0.02411   0.02044  -0.0050   1.0000   0.0024
  -9.750  -1.0295   0.02244   0.01855  -0.0044   1.0000   0.0025
  -9.500  -1.0083   0.02107   0.01699  -0.0039   1.0000   0.0026
  -9.250  -0.9859   0.01991   0.01567  -0.0035   1.0000   0.0027
  -9.000  -0.9629   0.01886   0.01447  -0.0031   1.0000   0.0029
  -8.750  -0.9394   0.01787   0.01332  -0.0027   1.0000   0.0031
  -8.500  -0.9156   0.01689   0.01218  -0.0024   1.0000   0.0033
  -8.250  -0.8913   0.01600   0.01114  -0.0020   1.0000   0.0034
  -8.000  -0.8666   0.01519   0.01019  -0.0017   1.0000   0.0035
  -7.750  -0.8422   0.01420   0.00903  -0.0013   1.0000   0.0037
  -7.500  -0.8173   0.01338   0.00808  -0.0010   1.0000   0.0040
  -7.250  -0.7916   0.01281   0.00743  -0.0008   1.0000   0.0044
  -7.000  -0.7656   0.01229   0.00684  -0.0006   1.0000   0.0047
  -6.750  -0.7394   0.01179   0.00627  -0.0004   1.0000   0.0051
  -6.500  -0.7131   0.01134   0.00575  -0.0003   1.0000   0.0054
  -6.250  -0.6867   0.01087   0.00520  -0.0001   1.0000   0.0061
  -6.000  -0.6602   0.01042   0.00472   0.0000   1.0000   0.0071
  -5.750  -0.6334   0.01006   0.00430   0.0001   1.0000   0.0081
  -5.500  -0.6065   0.00973   0.00391   0.0002   1.0000   0.0090
  -5.250  -0.5796   0.00939   0.00361   0.0003   1.0000   0.0119
  -5.000  -0.5524   0.00915   0.00341   0.0004   1.0000   0.0158
  -4.750  -0.5250   0.00903   0.00335   0.0004   1.0000   0.0208
  -4.500  -0.4975   0.00892   0.00322   0.0004   1.0000   0.0232
  -4.250  -0.4700   0.00885   0.00314   0.0004   1.0000   0.0246
  -4.000  -0.4425   0.00878   0.00309   0.0004   1.0000   0.0253
  -3.750  -0.4152   0.00868   0.00299   0.0005   1.0000   0.0256
  -3.500  -0.3880   0.00855   0.00284   0.0006   1.0000   0.0258
  -3.250  -0.3613   0.00821   0.00246   0.0007   1.0000   0.0267
  -3.000  -0.3345   0.00795   0.00216   0.0009   1.0000   0.0275
  -2.750  -0.3077   0.00775   0.00193   0.0012   1.0000   0.0275
  -2.500  -0.2813   0.00757   0.00174   0.0014   1.0000   0.0276
  -2.250  -0.2492   0.00740   0.00155   0.0004   0.9960   0.0279
  -2.000  -0.2166   0.00724   0.00137  -0.0007   0.9899   0.0287
  -1.750  -0.1840   0.00710   0.00124  -0.0017   0.9816   0.0311
  -1.500  -0.1519   0.00697   0.00115  -0.0027   0.9687   0.0355
  -1.250  -0.1250   0.00687   0.00106  -0.0022   0.9208   0.0620
  -1.000  -0.1030   0.00683   0.00095  -0.0007   0.8461   0.1116
  -0.750  -0.0774   0.00668   0.00085  -0.0003   0.7935   0.1847
  -0.500  -0.0521   0.00658   0.00077   0.0000   0.7043   0.2880
  -0.250  -0.0267   0.00672   0.00072   0.0001   0.5537   0.3876
   0.000   0.0000   0.00679   0.00071   0.0000   0.4593   0.4628
   0.250   0.0268   0.00672   0.00072  -0.0001   0.3873   0.5559
   0.500   0.0522   0.00658   0.00077   0.0000   0.2883   0.7041
   0.750   0.0775   0.00669   0.00085   0.0003   0.1835   0.7925
   1.000   0.1031   0.00684   0.00095   0.0007   0.1106   0.8453
   1.250   0.1249   0.00689   0.00106   0.0022   0.0542   0.9221
   1.500   0.1516   0.00697   0.00115   0.0027   0.0358   0.9675
   1.750   0.1840   0.00710   0.00124   0.0017   0.0312   0.9815
   2.000   0.2166   0.00724   0.00137   0.0007   0.0287   0.9898
   2.250   0.2493   0.00740   0.00155  -0.0005   0.0279   0.9960
   2.500   0.2813   0.00758   0.00174  -0.0015   0.0276   1.0000
   2.750   0.3078   0.00775   0.00194  -0.0012   0.0275   1.0000
   3.000   0.3346   0.00795   0.00216  -0.0010   0.0275   1.0000
   3.250   0.3613   0.00821   0.00246  -0.0008   0.0267   1.0000
   3.500   0.3880   0.00855   0.00285  -0.0006   0.0258   1.0000
   3.750   0.4152   0.00870   0.00301  -0.0005   0.0256   1.0000
   4.000   0.4426   0.00879   0.00309  -0.0004   0.0253   1.0000
   4.250   0.4700   0.00885   0.00315  -0.0004   0.0246   1.0000
   4.500   0.4976   0.00893   0.00322  -0.0004   0.0233   1.0000
   4.750   0.5250   0.00903   0.00335  -0.0004   0.0208   1.0000
   5.000   0.5525   0.00915   0.00341  -0.0004   0.0158   1.0000
   5.250   0.5796   0.00939   0.00361  -0.0003   0.0119   1.0000
   5.500   0.6065   0.00973   0.00391  -0.0002   0.0090   1.0000
   5.750   0.6335   0.01006   0.00430  -0.0001   0.0081   1.0000
   6.000   0.6602   0.01042   0.00472   0.0000   0.0071   1.0000
   6.250   0.6867   0.01087   0.00520   0.0001   0.0061   1.0000
   6.500   0.7131   0.01134   0.00574   0.0003   0.0054   1.0000
   6.750   0.7394   0.01179   0.00627   0.0004   0.0051   1.0000
   7.000   0.7656   0.01229   0.00684   0.0006   0.0047   1.0000
   7.250   0.7915   0.01281   0.00744   0.0008   0.0044   1.0000
   7.500   0.8173   0.01339   0.00808   0.0010   0.0041   1.0000
   7.750   0.8423   0.01419   0.00903   0.0013   0.0038   1.0000
   8.000   0.8666   0.01519   0.01019   0.0017   0.0035   1.0000
   8.250   0.8913   0.01599   0.01113   0.0020   0.0034   1.0000
   8.500   0.9156   0.01689   0.01219   0.0024   0.0033   1.0000
   8.750   0.9394   0.01786   0.01331   0.0027   0.0031   1.0000
   9.000   0.9629   0.01885   0.01446   0.0031   0.0029   1.0000
   9.250   0.9859   0.01991   0.01568   0.0035   0.0027   1.0000
   9.500   1.0083   0.02106   0.01698   0.0039   0.0026   1.0000
   9.750   1.0294   0.02245   0.01857   0.0044   0.0025   1.0000
  10.000   1.0492   0.02410   0.02042   0.0050   0.0024   1.0000
  10.250   1.0667   0.02616   0.02274   0.0057   0.0023   1.0000
  10.500   1.0799   0.02912   0.02602   0.0066   0.0023   1.0000
  10.750   1.0824   0.03433   0.03171   0.0077   0.0022   1.0000
  11.250   0.7602   0.12354   0.12196  -0.0373   0.0028   1.0000
  11.500   0.7569   0.12940   0.12781  -0.0397   0.0027   1.0000
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