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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 100,000
Max Cl/Cd: 49.48 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m9-il-100000-n5.txt
Download as CSV file: xf-m9-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M9 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2570   0.11729   0.11285  -0.0110   0.8474   0.0478
  -9.250  -0.2518   0.11470   0.11019  -0.0124   0.8260   0.0478
  -9.000  -0.2478   0.11204   0.10748  -0.0140   0.8090   0.0479
  -8.750  -0.2278   0.10632   0.10170  -0.0122   0.7950   0.0486
  -8.500  -0.2179   0.10323   0.09856  -0.0124   0.7819   0.0491
  -8.250  -0.2100   0.10038   0.09565  -0.0132   0.7700   0.0494
  -8.000  -0.2041   0.09761   0.09287  -0.0147   0.7585   0.0491
  -7.750  -0.1917   0.09512   0.09032  -0.0144   0.7477   0.0518
  -7.500  -0.1852   0.09281   0.08799  -0.0156   0.7374   0.0549
  -6.750  -0.1754   0.08156   0.07667  -0.0240   0.7114   0.0394
  -6.500  -0.1641   0.07843   0.07349  -0.0255   0.7027   0.0391
  -6.250  -0.1514   0.07521   0.07024  -0.0277   0.6933   0.0388
  -6.000  -0.1377   0.07149   0.06645  -0.0313   0.6855   0.0391
  -5.750  -0.1213   0.06937   0.06432  -0.0323   0.6753   0.0414
  -5.500  -0.1041   0.06668   0.06154  -0.0343   0.6671   0.0429
  -5.250  -0.0842   0.06293   0.05774  -0.0381   0.6575   0.0432
  -5.000  -0.0628   0.05902   0.05368  -0.0419   0.6500   0.0437
  -4.750  -0.0367   0.05435   0.04888  -0.0474   0.6409   0.0463
  -4.500  -0.0072   0.04772   0.04198  -0.0543   0.6346   0.0483
  -4.250   0.0158   0.04652   0.04073  -0.0546   0.6246   0.0499
  -4.000   0.0420   0.04419   0.03821  -0.0563   0.6170   0.0534
  -3.750   0.0802   0.03309   0.02634  -0.0656   0.6105   0.0584
  -3.500   0.1037   0.03407   0.02736  -0.0641   0.6014   0.0607
  -3.250   0.1353   0.02813   0.02068  -0.0677   0.5939   0.0653
  -3.000   0.1645   0.02455   0.01623  -0.0690   0.5866   0.0701
  -2.750   0.1911   0.02373   0.01526  -0.0687   0.5790   0.0728
  -2.500   0.2186   0.02284   0.01409  -0.0685   0.5714   0.0771
  -2.250   0.2467   0.02180   0.01251  -0.0682   0.5651   0.0817
  -2.000   0.2736   0.02122   0.01193  -0.0679   0.5571   0.0849
  -1.750   0.3008   0.02076   0.01128  -0.0674   0.5507   0.0900
  -1.500   0.3289   0.02029   0.01053  -0.0672   0.5437   0.0960
  -1.250   0.3559   0.01991   0.01015  -0.0668   0.5373   0.1011
  -1.000   0.3835   0.01960   0.00963  -0.0663   0.5324   0.1090
  -0.750   0.4110   0.01934   0.00938  -0.0661   0.5262   0.1168
  -0.500   0.4390   0.01914   0.00906  -0.0658   0.5204   0.1264
  -0.250   0.4663   0.01902   0.00895  -0.0653   0.5154   0.1388
   0.000   0.4935   0.01918   0.00924  -0.0649   0.5082   0.1516
   0.250   0.5196   0.01972   0.00990  -0.0641   0.5014   0.1654
   0.500   0.5458   0.02028   0.01048  -0.0634   0.4954   0.1799
   0.750   0.5743   0.02054   0.01050  -0.0630   0.4880   0.2182
   1.250   0.6277   0.02111   0.01078  -0.0619   0.4746   0.2512
   1.500   0.6543   0.02119   0.01076  -0.0615   0.4677   0.2626
   1.750   0.6810   0.02127   0.01067  -0.0610   0.4619   0.2726
   2.000   0.7074   0.02129   0.01073  -0.0607   0.4544   0.2819
   2.250   0.7339   0.02127   0.01064  -0.0603   0.4484   0.2904
   2.500   0.7606   0.02137   0.01069  -0.0600   0.4425   0.2977
   2.750   0.7872   0.02139   0.01072  -0.0597   0.4359   0.3035
   3.000   0.8138   0.02143   0.01068  -0.0593   0.4303   0.3108
   3.250   0.8403   0.02159   0.01084  -0.0591   0.4241   0.3161
   3.500   0.8665   0.02160   0.01090  -0.0588   0.4176   0.3199
   3.750   0.8932   0.02166   0.01087  -0.0584   0.4121   0.3210
   4.000   0.9200   0.02183   0.01112  -0.0583   0.4042   0.3214
   4.250   0.9472   0.02192   0.01116  -0.0581   0.3972   0.3219
   4.500   0.9741   0.02209   0.01136  -0.0579   0.3894   0.3222
   4.750   1.0007   0.02223   0.01150  -0.0577   0.3816   0.3221
   5.000   1.0269   0.02241   0.01169  -0.0575   0.3739   0.3217
   5.250   1.0527   0.02259   0.01191  -0.0572   0.3654   0.3215
   5.500   1.0781   0.02280   0.01215  -0.0568   0.3571   0.3213
   5.750   1.1029   0.02301   0.01239  -0.0564   0.3479   0.3211
   6.000   1.1272   0.02328   0.01271  -0.0559   0.3380   0.3210
   6.250   1.1509   0.02351   0.01293  -0.0553   0.3288   0.3210
   6.500   1.1739   0.02386   0.01336  -0.0548   0.3179   0.3210
   6.750   1.1965   0.02421   0.01371  -0.0541   0.3086   0.3210
   7.000   1.2183   0.02462   0.01414  -0.0534   0.2993   0.3212
   7.250   1.2398   0.02508   0.01464  -0.0527   0.2913   0.3217
   7.500   1.2607   0.02556   0.01515  -0.0519   0.2839   0.3224
   7.750   1.2811   0.02609   0.01570  -0.0511   0.2775   0.3231
   8.000   1.3010   0.02668   0.01635  -0.0502   0.2714   0.3239
   8.250   1.3204   0.02725   0.01691  -0.0493   0.2666   0.3246
   8.500   1.3396   0.02792   0.01765  -0.0484   0.2617   0.3252
   8.750   1.3579   0.02861   0.01841  -0.0475   0.2569   0.3256
   9.000   1.3756   0.02928   0.01910  -0.0465   0.2525   0.3260
   9.250   1.3928   0.03003   0.01987  -0.0455   0.2483   0.3263
   9.500   1.4085   0.03086   0.02082  -0.0444   0.2437   0.3269
   9.750   1.4235   0.03168   0.02169  -0.0432   0.2397   0.3274
  10.000   1.4395   0.03246   0.02246  -0.0421   0.2364   0.3280
  10.250   1.4542   0.03336   0.02345  -0.0410   0.2333   0.3287
  10.500   1.4649   0.03438   0.02462  -0.0395   0.2305   0.3292
  10.750   1.4756   0.03545   0.02581  -0.0381   0.2277   0.3300
  11.000   1.4872   0.03654   0.02699  -0.0369   0.2253   0.3308
  11.250   1.4996   0.03760   0.02813  -0.0358   0.2227   0.3317
  11.500   1.5161   0.03848   0.02904  -0.0350   0.2202   0.3328
  11.750   1.5241   0.03990   0.03060  -0.0339   0.2175   0.3339
  12.000   1.5270   0.04170   0.03260  -0.0329   0.2150   0.3349
  12.250   1.5306   0.04354   0.03462  -0.0322   0.2121   0.3366
  12.500   1.5367   0.04525   0.03647  -0.0315   0.2095   0.3382
  12.750   1.5455   0.04679   0.03812  -0.0309   0.2071   0.3409
  13.000   1.5597   0.04789   0.03928  -0.0303   0.2044   0.3441
  13.250   1.5626   0.04998   0.04151  -0.0298   0.2017   0.3465
  13.500   1.5498   0.05359   0.04539  -0.0299   0.1990   0.3478
  14.000   1.5339   0.06024   0.05237  -0.0305   0.1916   0.3519
  14.250   1.5426   0.06154   0.05363  -0.0303   0.1862   0.3572
  14.500   1.5170   0.06750   0.05989  -0.0319   0.1837   0.3571
  14.750   1.4897   0.07415   0.06678  -0.0341   0.1811   0.3569
  15.000   1.4608   0.08150   0.07435  -0.0369   0.1782   0.3564
  15.500   1.4524   0.08891   0.08193  -0.0393   0.1699   0.3651
  15.750   1.3787   0.10544   0.09873  -0.0466   0.1696   0.3544
  16.000   1.1859   0.14987   0.14317  -0.0694   0.1530   0.3351
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