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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 500,000
Max Cl/Cd: 81.16 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m9-il-500000-n5.txt
Download as CSV file: xf-m9-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2619   0.08945   0.08612  -0.0105   0.6357   0.0111
  -8.250  -0.2696   0.08407   0.08076  -0.0126   0.6309   0.0115
  -7.750  -0.3601   0.03647   0.03250  -0.0566   0.6367   0.0142
  -7.500  -0.3419   0.02626   0.02159  -0.0644   0.6313   0.0147
  -7.250  -0.3173   0.02273   0.01774  -0.0664   0.6228   0.0153
  -7.000  -0.2916   0.02051   0.01526  -0.0674   0.6143   0.0161
  -6.750  -0.2652   0.01897   0.01349  -0.0677   0.6038   0.0169
  -6.500  -0.2385   0.01773   0.01202  -0.0678   0.5928   0.0179
  -6.250  -0.2117   0.01666   0.01075  -0.0678   0.5811   0.0189
  -6.000  -0.1845   0.01583   0.00978  -0.0677   0.5690   0.0203
  -5.750  -0.1570   0.01520   0.00898  -0.0675   0.5580   0.0219
  -5.500  -0.1296   0.01460   0.00824  -0.0673   0.5475   0.0235
  -5.250  -0.1018   0.01414   0.00768  -0.0671   0.5371   0.0252
  -5.000  -0.0740   0.01378   0.00716  -0.0668   0.5278   0.0270
  -4.750  -0.0463   0.01340   0.00669  -0.0665   0.5180   0.0287
  -4.500  -0.0183   0.01315   0.00634  -0.0662   0.5092   0.0307
  -4.250   0.0096   0.01292   0.00599  -0.0659   0.5004   0.0325
  -4.000   0.0375   0.01264   0.00563  -0.0655   0.4931   0.0343
  -3.750   0.0656   0.01244   0.00537  -0.0652   0.4858   0.0363
  -3.500   0.0937   0.01229   0.00511  -0.0649   0.4794   0.0383
  -3.250   0.1219   0.01211   0.00486  -0.0646   0.4734   0.0399
  -3.000   0.1498   0.01189   0.00460  -0.0643   0.4672   0.0423
  -2.750   0.1780   0.01176   0.00440  -0.0640   0.4611   0.0445
  -2.500   0.2061   0.01163   0.00419  -0.0637   0.4542   0.0465
  -2.250   0.2342   0.01152   0.00399  -0.0633   0.4472   0.0484
  -2.000   0.2623   0.01134   0.00379  -0.0630   0.4407   0.0514
  -1.750   0.2904   0.01124   0.00364  -0.0627   0.4338   0.0540
  -1.500   0.3185   0.01118   0.00350  -0.0624   0.4286   0.0567
  -1.250   0.3468   0.01106   0.00336  -0.0621   0.4245   0.0604
  -1.000   0.3750   0.01097   0.00327  -0.0618   0.4197   0.0650
  -0.750   0.4030   0.01094   0.00318  -0.0615   0.4146   0.0690
  -0.500   0.4311   0.01087   0.00311  -0.0612   0.4102   0.0750
  -0.250   0.4593   0.01083   0.00306  -0.0610   0.4057   0.0808
   0.000   0.4873   0.01078   0.00301  -0.0607   0.4008   0.0877
   0.250   0.5152   0.01080   0.00298  -0.0604   0.3962   0.0941
   0.500   0.5432   0.01077   0.00295  -0.0601   0.3919   0.1004
   0.750   0.5712   0.01076   0.00294  -0.0599   0.3870   0.1074
   1.000   0.5991   0.01079   0.00295  -0.0596   0.3819   0.1134
   1.250   0.6268   0.01080   0.00295  -0.0593   0.3769   0.1233
   1.500   0.6545   0.01073   0.00294  -0.0590   0.3722   0.1411
   1.750   0.6835   0.01141   0.00379  -0.0588   0.3670   0.2034
   2.000   0.7111   0.01141   0.00369  -0.0586   0.3620   0.2163
   2.250   0.7392   0.01164   0.00391  -0.0583   0.3576   0.2210
   2.500   0.7670   0.01181   0.00405  -0.0580   0.3521   0.2255
   2.750   0.7945   0.01196   0.00413  -0.0578   0.3459   0.2285
   3.000   0.8221   0.01208   0.00427  -0.0575   0.3395   0.2301
   3.250   0.8494   0.01223   0.00440  -0.0573   0.3314   0.2319
   3.500   0.8768   0.01235   0.00450  -0.0570   0.3240   0.2339
   3.750   0.9039   0.01248   0.00458  -0.0568   0.3148   0.2357
   4.000   0.9309   0.01263   0.00468  -0.0565   0.3049   0.2374
   4.250   0.9576   0.01278   0.00477  -0.0563   0.2923   0.2383
   4.500   0.9838   0.01296   0.00489  -0.0560   0.2758   0.2389
   4.750   1.0094   0.01323   0.00508  -0.0557   0.2561   0.2395
   5.000   1.0347   0.01354   0.00532  -0.0554   0.2405   0.2406
   5.250   1.0601   0.01383   0.00557  -0.0550   0.2297   0.2417
   5.500   1.0852   0.01416   0.00585  -0.0547   0.2202   0.2430
   5.750   1.1107   0.01440   0.00609  -0.0543   0.2137   0.2444
   6.000   1.1359   0.01466   0.00633  -0.0540   0.2081   0.2450
   6.250   1.1607   0.01494   0.00660  -0.0536   0.2030   0.2451
   6.500   1.1863   0.01510   0.00680  -0.0532   0.1998   0.2452
   6.750   1.2115   0.01530   0.00702  -0.0529   0.1963   0.2453
   7.000   1.2361   0.01554   0.00728  -0.0525   0.1928   0.2454
   7.250   1.2604   0.01581   0.00757  -0.0520   0.1899   0.2455
   7.500   1.2843   0.01610   0.00788  -0.0515   0.1870   0.2456
   7.750   1.3090   0.01629   0.00813  -0.0511   0.1854   0.2458
   8.000   1.3333   0.01651   0.00841  -0.0507   0.1835   0.2459
   8.250   1.3572   0.01675   0.00870  -0.0502   0.1814   0.2461
   8.500   1.3806   0.01701   0.00902  -0.0497   0.1792   0.2463
   8.750   1.4034   0.01732   0.00938  -0.0491   0.1770   0.2465
   9.000   1.4255   0.01766   0.00976  -0.0484   0.1748   0.2467
   9.250   1.4465   0.01806   0.01019  -0.0477   0.1719   0.2468
   9.500   1.4686   0.01836   0.01055  -0.0470   0.1699   0.2471
   9.750   1.4904   0.01865   0.01092  -0.0463   0.1666   0.2473
  10.000   1.5104   0.01904   0.01134  -0.0455   0.1617   0.2476
  10.250   1.5280   0.01957   0.01188  -0.0444   0.1572   0.2480
  10.500   1.5471   0.01996   0.01233  -0.0434   0.1530   0.2484
  10.750   1.5634   0.02047   0.01287  -0.0422   0.1467   0.2488
  11.000   1.5743   0.02109   0.01352  -0.0402   0.1417   0.2490
  11.250   1.5834   0.02173   0.01421  -0.0380   0.1356   0.2493
  11.500   1.5880   0.02277   0.01525  -0.0358   0.1290   0.2493
  11.750   1.5920   0.02404   0.01654  -0.0341   0.1188   0.2497
  12.000   1.5799   0.02675   0.01910  -0.0321   0.0946   0.2498
  12.250   1.5620   0.03035   0.02260  -0.0307   0.0732   0.2499
  12.500   1.5556   0.03315   0.02541  -0.0298   0.0660   0.2498
  12.750   1.5497   0.03603   0.02834  -0.0292   0.0601   0.2501
  13.000   1.5506   0.03836   0.03075  -0.0288   0.0579   0.2502
  13.250   1.5473   0.04122   0.03367  -0.0286   0.0549   0.2503
  13.500   1.5410   0.04449   0.03701  -0.0286   0.0517   0.2505
  13.750   1.5388   0.04743   0.04004  -0.0287   0.0498   0.2506
  14.000   1.5378   0.05030   0.04301  -0.0289   0.0477   0.2510
  14.250   1.5316   0.05388   0.04666  -0.0294   0.0440   0.2513
  14.500   1.5229   0.05792   0.05076  -0.0301   0.0406   0.2513
  14.750   1.5186   0.06157   0.05449  -0.0309   0.0372   0.2515
  15.000   1.4928   0.06830   0.06118  -0.0328   0.0214   0.2517
  15.250   1.4767   0.07391   0.06684  -0.0345   0.0180   0.2516
  15.500   1.4628   0.07938   0.07241  -0.0363   0.0157   0.2518
  15.750   1.4512   0.08467   0.07781  -0.0381   0.0144   0.2517
  16.000   1.4397   0.09008   0.08334  -0.0400   0.0134   0.2519
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