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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 200,000
Max Cl/Cd: 63.08 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m9-il-200000.txt
Download as CSV file: xf-m9-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2305   0.09596   0.09248  -0.0098   0.7893   0.0499
  -7.750  -0.2412   0.09526   0.09178  -0.0132   0.7760   0.0508
  -7.500  -0.2427   0.09344   0.08993  -0.0175   0.7647   0.0510
  -7.250  -0.2293   0.08850   0.08492  -0.0148   0.7546   0.0517
  -7.000  -0.2138   0.08534   0.08173  -0.0133   0.7427   0.0526
  -6.750  -0.2024   0.08292   0.07926  -0.0134   0.7317   0.0540
  -6.500  -0.1923   0.08058   0.07685  -0.0147   0.7213   0.0564
  -6.250  -0.1799   0.07853   0.07474  -0.0263   0.7111   0.0600
  -6.000  -0.1693   0.07406   0.07021  -0.0270   0.7026   0.0608
  -5.750  -0.1556   0.07126   0.06741  -0.0248   0.6914   0.0618
  -5.500  -0.1397   0.06884   0.06494  -0.0247   0.6813   0.0634
  -5.250  -0.1221   0.06629   0.06230  -0.0264   0.6716   0.0658
  -5.000  -0.0865   0.06135   0.05717  -0.0399   0.6626   0.0712
  -4.750  -0.0767   0.05896   0.05475  -0.0362   0.6535   0.0726
  -4.500  -0.0587   0.05711   0.05289  -0.0353   0.6421   0.0753
  -4.000  -0.0003   0.04958   0.04504  -0.0451   0.6248   0.0848
  -3.750   0.0184   0.04802   0.04342  -0.0438   0.6164   0.0872
  -3.500   0.0625   0.03487   0.02963  -0.0553   0.6112   0.0721
  -3.250   0.0926   0.02398   0.01746  -0.0600   0.6060   0.0701
  -3.000   0.1181   0.02140   0.01438  -0.0600   0.5982   0.0727
  -2.750   0.1448   0.02091   0.01387  -0.0596   0.5893   0.0764
  -2.500   0.1723   0.01970   0.01227  -0.0592   0.5815   0.0797
  -2.250   0.2003   0.01889   0.01102  -0.0588   0.5734   0.0835
  -2.000   0.2270   0.01790   0.00992  -0.0584   0.5668   0.0875
  -1.750   0.2549   0.01737   0.00926  -0.0580   0.5592   0.0920
  -1.500   0.2831   0.01715   0.00874  -0.0575   0.5530   0.0969
  -1.250   0.3104   0.01626   0.00786  -0.0572   0.5454   0.1030
  -1.000   0.3383   0.01593   0.00739  -0.0568   0.5382   0.1100
  -0.750   0.3657   0.01542   0.00687  -0.0564   0.5311   0.1182
  -0.500   0.3936   0.01516   0.00652  -0.0559   0.5239   0.1273
  -0.250   0.4208   0.01490   0.00624  -0.0554   0.5183   0.1404
   0.000   0.4486   0.01473   0.00620  -0.0551   0.5112   0.1573
   0.250   0.4762   0.01539   0.00707  -0.0544   0.5052   0.1767
   0.500   0.5039   0.01617   0.00784  -0.0538   0.4999   0.1984
   0.750   0.5319   0.01681   0.00841  -0.0532   0.4928   0.2259
   1.000   0.5590   0.01734   0.00878  -0.0526   0.4867   0.2467
   1.250   0.5858   0.01755   0.00904  -0.0521   0.4807   0.2620
   1.500   0.6126   0.01764   0.00912  -0.0517   0.4747   0.2787
   1.750   0.6394   0.01769   0.00908  -0.0513   0.4699   0.2938
   2.000   0.6662   0.01766   0.00905  -0.0510   0.4646   0.3064
   2.250   0.6931   0.01755   0.00896  -0.0507   0.4585   0.3173
   2.500   0.7206   0.01774   0.00898  -0.0503   0.4531   0.3256
   2.750   0.7472   0.01749   0.00880  -0.0501   0.4472   0.3331
   3.000   0.7744   0.01756   0.00883  -0.0497   0.4407   0.3392
   3.250   0.8014   0.01744   0.00865  -0.0494   0.4355   0.3451
   3.500   0.8283   0.01744   0.00871  -0.0492   0.4290   0.3505
   3.750   0.8555   0.01744   0.00869  -0.0489   0.4224   0.3514
   4.000   0.8826   0.01756   0.00872  -0.0485   0.4164   0.3544
   4.250   0.9092   0.01748   0.00872  -0.0483   0.4084   0.3579
   4.500   0.9360   0.01746   0.00862  -0.0479   0.4015   0.3598
   4.750   0.9626   0.01747   0.00872  -0.0476   0.3921   0.3587
   5.000   0.9891   0.01756   0.00872  -0.0472   0.3839   0.3571
   5.250   1.0154   0.01762   0.00885  -0.0468   0.3732   0.3558
   5.500   1.0413   0.01765   0.00890  -0.0464   0.3625   0.3551
   5.750   1.0669   0.01772   0.00892  -0.0460   0.3514   0.3546
   6.000   1.0921   0.01782   0.00904  -0.0456   0.3382   0.3544
   6.250   1.1171   0.01800   0.00924  -0.0451   0.3249   0.3541
   6.500   1.1417   0.01824   0.00949  -0.0447   0.3129   0.3533
   6.750   1.1659   0.01856   0.00974  -0.0442   0.3029   0.3525
   7.000   1.1901   0.01887   0.01007  -0.0437   0.2932   0.3518
   7.250   1.2139   0.01925   0.01045  -0.0432   0.2852   0.3512
   7.500   1.2376   0.01962   0.01083  -0.0427   0.2780   0.3507
   7.750   1.2609   0.02006   0.01124  -0.0421   0.2716   0.3502
   8.000   1.2842   0.02044   0.01168  -0.0416   0.2650   0.3499
   8.500   1.3302   0.02137   0.01266  -0.0406   0.2544   0.3495
   8.750   1.3530   0.02184   0.01318  -0.0400   0.2502   0.3494
   9.000   1.3756   0.02238   0.01372  -0.0394   0.2466   0.3495
   9.250   1.3984   0.02302   0.01434  -0.0389   0.2434   0.3496
   9.500   1.4201   0.02356   0.01502  -0.0382   0.2405   0.3499
   9.750   1.4417   0.02413   0.01569  -0.0375   0.2375   0.3502
  10.000   1.4630   0.02470   0.01632  -0.0369   0.2342   0.3508
  10.250   1.4848   0.02535   0.01694  -0.0363   0.2308   0.3519
  10.500   1.5059   0.02610   0.01775  -0.0357   0.2276   0.3533
  10.750   1.5238   0.02673   0.01856  -0.0347   0.2246   0.3544
  11.000   1.5414   0.02735   0.01927  -0.0338   0.2206   0.3554
  11.250   1.5597   0.02798   0.01990  -0.0329   0.2163   0.3565
  11.500   1.5782   0.02882   0.02076  -0.0321   0.2123   0.3578
  11.750   1.5898   0.02954   0.02170  -0.0306   0.2091   0.3590
  12.000   1.6015   0.03026   0.02254  -0.0291   0.2053   0.3605
  12.250   1.6124   0.03095   0.02326  -0.0274   0.2015   0.3623
  12.500   1.6253   0.03185   0.02415  -0.0261   0.1972   0.3647
  12.750   1.6225   0.03296   0.02548  -0.0236   0.1941   0.3661
  13.000   1.6254   0.03416   0.02683  -0.0221   0.1909   0.3683
  13.500   1.6415   0.03644   0.02919  -0.0201   0.1837   0.3760
  13.750   1.6399   0.03828   0.03124  -0.0193   0.1806   0.3818
  14.000   1.6373   0.04037   0.03354  -0.0188   0.1772   0.3904
  14.250   1.6542   0.04224   0.03631  -0.0229   0.1721   1.0000
  14.500   1.6584   0.04400   0.03802  -0.0225   0.1681   1.0000
  14.750   1.6510   0.04709   0.04138  -0.0228   0.1648   1.0000
  15.000   1.6456   0.05013   0.04461  -0.0233   0.1607   1.0000
  15.250   1.6411   0.05315   0.04771  -0.0239   0.1566   1.0000
  15.500   1.6371   0.05620   0.05083  -0.0244   0.1529   1.0000
  15.750   1.6263   0.06040   0.05527  -0.0256   0.1479   1.0000
  16.000   1.6185   0.06436   0.05933  -0.0268   0.1432   1.0000
  16.250   1.6100   0.06857   0.06364  -0.0282   0.1386   1.0000
  16.500   1.5993   0.07333   0.06858  -0.0298   0.1332   1.0000
  16.750   1.5860   0.07850   0.07380  -0.0318   0.1275   1.0000
  17.000   1.5711   0.08415   0.07962  -0.0339   0.1203   1.0000
  17.250   1.5533   0.09029   0.08584  -0.0363   0.1138   1.0000
  17.500   1.5348   0.09673   0.09238  -0.0388   0.1067   1.0000
  17.750   1.5131   0.10380   0.09952  -0.0418   0.1001   1.0000
  18.000   1.4890   0.11147   0.10725  -0.0451   0.0942   1.0000
  18.250   1.4655   0.11927   0.11513  -0.0487   0.0899   1.0000
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