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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 200,000
Max Cl/Cd: 63.84 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m9-il-200000-n5.txt
Download as CSV file: xf-m9-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2204   0.09182   0.08769  -0.0113   0.6872   0.0213
  -7.750  -0.2161   0.08866   0.08454  -0.0126   0.6800   0.0215
  -7.500  -0.2122   0.08561   0.08149  -0.0138   0.6725   0.0215
  -7.250  -0.2093   0.08282   0.07869  -0.0148   0.6650   0.0213
  -7.000  -0.2044   0.07929   0.07516  -0.0172   0.6573   0.0215
  -6.750  -0.1959   0.07587   0.07170  -0.0197   0.6503   0.0215
  -6.500  -0.1877   0.07100   0.06682  -0.0241   0.6430   0.0221
  -6.250  -0.1746   0.06690   0.06267  -0.0280   0.6356   0.0230
  -6.000  -0.1559   0.06513   0.06087  -0.0295   0.6263   0.0238
  -5.750  -0.1378   0.06168   0.05735  -0.0329   0.6181   0.0249
  -5.500  -0.1180   0.05638   0.05196  -0.0382   0.6100   0.0257
  -5.250  -0.0884   0.02527   0.01935  -0.0666   0.6128   0.0324
  -5.000  -0.0614   0.02282   0.01654  -0.0676   0.6029   0.0342
  -4.750  -0.0340   0.02199   0.01554  -0.0677   0.5923   0.0363
  -4.500  -0.0069   0.01995   0.01288  -0.0681   0.5829   0.0395
  -4.250   0.0200   0.01930   0.01212  -0.0679   0.5725   0.0414
  -4.000   0.0473   0.01891   0.01158  -0.0676   0.5635   0.0439
  -3.750   0.0749   0.01808   0.01042  -0.0673   0.5543   0.0469
  -3.500   0.1020   0.01744   0.00957  -0.0670   0.5461   0.0494
  -3.250   0.1295   0.01714   0.00919  -0.0667   0.5373   0.0520
  -3.000   0.1570   0.01669   0.00854  -0.0663   0.5296   0.0547
  -2.750   0.1849   0.01626   0.00787  -0.0659   0.5215   0.0575
  -2.250   0.2399   0.01558   0.00704  -0.0652   0.5080   0.0629
  -2.000   0.2677   0.01536   0.00669  -0.0648   0.5018   0.0667
  -1.750   0.2954   0.01514   0.00634  -0.0644   0.4965   0.0702
  -1.500   0.3232   0.01497   0.00618  -0.0641   0.4904   0.0739
  -1.250   0.3509   0.01486   0.00597  -0.0637   0.4840   0.0785
  -1.000   0.3786   0.01477   0.00581  -0.0633   0.4775   0.0838
  -0.750   0.4064   0.01469   0.00570  -0.0630   0.4699   0.0899
  -0.500   0.4340   0.01466   0.00554  -0.0626   0.4638   0.0961
  -0.250   0.4618   0.01457   0.00548  -0.0623   0.4580   0.1042
   0.000   0.4896   0.01453   0.00537  -0.0620   0.4526   0.1120
   0.250   0.5172   0.01449   0.00531  -0.0616   0.4478   0.1223
   0.500   0.5449   0.01446   0.00530  -0.0613   0.4425   0.1348
   0.750   0.5725   0.01470   0.00569  -0.0609   0.4362   0.1544
   1.000   0.5990   0.01554   0.00670  -0.0603   0.4307   0.1806
   1.250   0.6277   0.01555   0.00645  -0.0601   0.4254   0.2207
   1.500   0.6552   0.01585   0.00669  -0.0597   0.4199   0.2313
   1.750   0.6825   0.01608   0.00680  -0.0593   0.4147   0.2391
   2.000   0.7095   0.01624   0.00694  -0.0589   0.4097   0.2450
   2.250   0.7368   0.01633   0.00701  -0.0586   0.4041   0.2503
   2.500   0.7638   0.01639   0.00705  -0.0583   0.3986   0.2538
   2.750   0.7908   0.01650   0.00709  -0.0580   0.3934   0.2580
   3.000   0.8180   0.01653   0.00714  -0.0577   0.3874   0.2616
   3.250   0.8447   0.01657   0.00719  -0.0574   0.3818   0.2650
   3.500   0.8715   0.01664   0.00723  -0.0571   0.3766   0.2667
   3.750   0.8986   0.01669   0.00730  -0.0569   0.3703   0.2682
   4.000   0.9251   0.01683   0.00740  -0.0566   0.3640   0.2713
   4.250   0.9516   0.01684   0.00746  -0.0563   0.3573   0.2747
   4.500   0.9779   0.01691   0.00755  -0.0560   0.3491   0.2774
   4.750   1.0041   0.01700   0.00766  -0.0557   0.3408   0.2783
   5.000   1.0300   0.01711   0.00777  -0.0554   0.3311   0.2785
   5.250   1.0559   0.01724   0.00791  -0.0550   0.3210   0.2784
   5.500   1.0812   0.01741   0.00807  -0.0546   0.3104   0.2782
   5.750   1.1063   0.01761   0.00825  -0.0543   0.2983   0.2780
   6.000   1.1310   0.01784   0.00848  -0.0538   0.2856   0.2779
   6.250   1.1550   0.01812   0.00875  -0.0534   0.2733   0.2778
   6.500   1.1785   0.01846   0.00905  -0.0529   0.2623   0.2778
   6.750   1.2016   0.01884   0.00940  -0.0523   0.2527   0.2778
   7.000   1.2243   0.01923   0.00979  -0.0517   0.2447   0.2778
   7.250   1.2461   0.01969   0.01024  -0.0511   0.2373   0.2778
   7.500   1.2678   0.02014   0.01069  -0.0504   0.2310   0.2779
   7.750   1.2893   0.02060   0.01117  -0.0497   0.2255   0.2779
   8.000   1.3093   0.02115   0.01172  -0.0489   0.2207   0.2780
   8.250   1.3302   0.02161   0.01224  -0.0482   0.2172   0.2782
   8.500   1.3511   0.02205   0.01277  -0.0474   0.2140   0.2784
   8.750   1.3712   0.02255   0.01333  -0.0466   0.2109   0.2786
   9.000   1.3901   0.02311   0.01395  -0.0457   0.2078   0.2789
   9.250   1.4076   0.02375   0.01461  -0.0447   0.2051   0.2794
   9.500   1.4245   0.02440   0.01530  -0.0435   0.2026   0.2801
   9.750   1.4426   0.02492   0.01594  -0.0425   0.2005   0.2807
  10.000   1.4592   0.02549   0.01664  -0.0414   0.1981   0.2813
  10.250   1.4722   0.02611   0.01736  -0.0398   0.1955   0.2816
  10.500   1.4834   0.02686   0.01818  -0.0381   0.1932   0.2819
  10.750   1.4943   0.02773   0.01911  -0.0366   0.1912   0.2821
  11.000   1.5052   0.02868   0.02012  -0.0353   0.1894   0.2824
  11.250   1.5153   0.02975   0.02123  -0.0341   0.1872   0.2827
  11.500   1.5262   0.03077   0.02239  -0.0332   0.1848   0.2829
  11.750   1.5353   0.03197   0.02374  -0.0324   0.1810   0.2833
  12.000   1.5421   0.03340   0.02526  -0.0318   0.1767   0.2836
  12.250   1.5467   0.03510   0.02699  -0.0311   0.1729   0.2840
  12.500   1.5530   0.03674   0.02874  -0.0307   0.1692   0.2841
  12.750   1.5605   0.03835   0.03051  -0.0303   0.1655   0.2846
  13.000   1.5649   0.04028   0.03254  -0.0301   0.1615   0.2849
  13.250   1.5672   0.04245   0.03477  -0.0299   0.1582   0.2851
  13.500   1.5704   0.04462   0.03706  -0.0298   0.1546   0.2855
  13.750   1.5736   0.04688   0.03947  -0.0298   0.1498   0.2859
  14.000   1.5725   0.04967   0.04234  -0.0301   0.1450   0.2864
  14.250   1.5714   0.05252   0.04528  -0.0304   0.1407   0.2870
  14.500   1.5696   0.05557   0.04845  -0.0309   0.1336   0.2873
  14.750   1.5638   0.05919   0.05215  -0.0317   0.1274   0.2877
  15.250   1.5454   0.06785   0.06092  -0.0340   0.1060   0.2885
  15.500   1.5272   0.07367   0.06671  -0.0359   0.0928   0.2886
  15.750   1.5016   0.08078   0.07379  -0.0385   0.0808   0.2884
  16.000   1.4799   0.08755   0.08059  -0.0409   0.0736   0.2885
  16.250   1.4635   0.09370   0.08682  -0.0432   0.0701   0.2888
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