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MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 78 14.47% (mh78-il)
Reynolds number: 50,000
Max Cl/Cd: 18.4 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh78-il-50000-n5.txt
Download as CSV file: xf-mh78-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 78  14.47%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5402   0.10038   0.09416   0.0159   1.0000   0.0490
  -9.750  -0.5454   0.09401   0.08785   0.0119   1.0000   0.0485
  -9.500  -0.5569   0.08597   0.07982   0.0058   1.0000   0.0478
  -9.250  -0.5802   0.07789   0.07169  -0.0004   1.0000   0.0469
  -9.000  -0.6084   0.07132   0.06498  -0.0037   1.0000   0.0460
  -8.750  -0.6341   0.06615   0.05960  -0.0039   1.0000   0.0455
  -8.500  -0.6451   0.06189   0.05513  -0.0036   1.0000   0.0456
  -8.250  -0.6486   0.05809   0.05111  -0.0030   1.0000   0.0458
  -8.000  -0.6464   0.05465   0.04743  -0.0023   1.0000   0.0465
  -7.750  -0.6410   0.05128   0.04378  -0.0015   1.0000   0.0472
  -7.500  -0.6323   0.04801   0.04017  -0.0007   1.0000   0.0480
  -7.250  -0.6201   0.04482   0.03658   0.0001   1.0000   0.0489
  -7.000  -0.6038   0.04180   0.03310   0.0006   1.0000   0.0498
  -6.750  -0.5717   0.03949   0.03061  -0.0010   0.8922   0.0509
  -6.500  -0.5497   0.03781   0.02862   0.0002   0.8394   0.0521
  -6.250  -0.5313   0.03633   0.02677   0.0023   0.8019   0.0538
  -6.000  -0.5115   0.03485   0.02482   0.0044   0.7707   0.0563
  -5.750  -0.4917   0.03380   0.02367   0.0062   0.7439   0.0589
  -5.500  -0.4685   0.03258   0.02216   0.0076   0.7188   0.0624
  -5.250  -0.4449   0.03141   0.02087   0.0090   0.6959   0.0656
  -5.000  -0.4204   0.03040   0.01962   0.0103   0.6747   0.0710
  -4.750  -0.3965   0.02944   0.01862   0.0114   0.6547   0.0773
  -4.250  -0.3469   0.02760   0.01659   0.0134   0.6183   0.0994
  -4.000  -0.3229   0.02664   0.01570   0.0144   0.6020   0.1199
  -3.750  -0.3001   0.02556   0.01485   0.0155   0.5871   0.1612
  -3.500  -0.2786   0.02444   0.01417   0.0164   0.5714   0.2385
  -3.250  -0.2597   0.02346   0.01369   0.0180   0.5575   0.3394
  -3.000  -0.2440   0.02254   0.01338   0.0206   0.5460   0.4612
  -2.750  -0.2139   0.02192   0.01374   0.0226   0.5304   0.6477
  -2.500  -0.1567   0.02273   0.01462   0.0214   0.5128   0.7820
  -2.250  -0.1226   0.02333   0.01489   0.0222   0.4999   0.8363
  -2.000  -0.0839   0.02384   0.01504   0.0218   0.4867   0.8736
  -1.750  -0.0383   0.02427   0.01515   0.0196   0.4724   0.9030
  -1.500   0.0085   0.02455   0.01508   0.0170   0.4601   0.9283
  -1.250   0.0603   0.02467   0.01486   0.0131   0.4474   0.9512
  -1.000   0.1137   0.02473   0.01467   0.0085   0.4345   0.9729
  -0.750   0.1685   0.02455   0.01412   0.0034   0.4240   0.9919
  -0.500   0.2065   0.02452   0.01397   0.0008   0.4132   1.0000
  -0.250   0.2276   0.02458   0.01377   0.0017   0.4069   1.0000
   0.000   0.2509   0.02482   0.01396   0.0019   0.3987   1.0000
   0.250   0.2733   0.02500   0.01399   0.0025   0.3917   1.0000
   0.500   0.2951   0.02516   0.01391   0.0034   0.3862   1.0000
   0.750   0.3187   0.02556   0.01434   0.0036   0.3781   1.0000
   1.000   0.3410   0.02584   0.01448   0.0043   0.3722   1.0000
   1.250   0.3628   0.02607   0.01450   0.0052   0.3677   1.0000
   1.500   0.3861   0.02669   0.01520   0.0053   0.3603   1.0000
   1.750   0.4083   0.02709   0.01552   0.0060   0.3546   1.0000
   2.000   0.4300   0.02738   0.01563   0.0070   0.3503   1.0000
   2.250   0.4524   0.02811   0.01641   0.0072   0.3444   1.0000
   2.500   0.4742   0.02878   0.01709   0.0077   0.3387   1.0000
   2.750   0.4957   0.02922   0.01744   0.0086   0.3344   1.0000
   3.000   0.5171   0.02954   0.01758   0.0097   0.3309   1.0000
   3.250   0.5374   0.03078   0.01903   0.0097   0.3246   1.0000
   3.500   0.5575   0.03161   0.01987   0.0103   0.3198   1.0000
   3.750   0.5780   0.03217   0.02036   0.0113   0.3161   1.0000
   4.000   0.5990   0.03255   0.02059   0.0125   0.3131   1.0000
   4.250   0.6148   0.03432   0.02263   0.0125   0.3072   1.0000
   4.500   0.6316   0.03552   0.02391   0.0132   0.3026   1.0000
   4.750   0.6500   0.03630   0.02466   0.0142   0.2991   1.0000
   5.000   0.6697   0.03682   0.02508   0.0155   0.2965   1.0000
   5.250   0.6800   0.03891   0.02737   0.0160   0.2919   1.0000
   5.500   0.6862   0.04129   0.02994   0.0164   0.2868   1.0000
   5.750   0.6981   0.04266   0.03134   0.0175   0.2832   1.0000
   6.000   0.7143   0.04347   0.03211   0.0189   0.2805   1.0000
   6.250   0.7338   0.04396   0.03251   0.0203   0.2785   1.0000
   6.500   0.6723   0.05318   0.04224   0.0191   0.2704   1.0000
   6.750   0.6581   0.05690   0.04598   0.0194   0.2661   1.0000
   7.000   0.6715   0.05778   0.04681   0.0209   0.2637   1.0000
   7.250   0.6928   0.05792   0.04690   0.0226   0.2620   1.0000
   7.750   0.5705   0.07772   0.06676   0.0149   0.2484   1.0000
   8.000   0.5880   0.07858   0.06758   0.0160   0.2463   1.0000
   8.250   0.5651   0.08472   0.07372   0.0135   0.2423   1.0000
   8.500   0.5495   0.08994   0.07895   0.0115   0.2387   1.0000
   8.750   0.5504   0.09311   0.08212   0.0108   0.2355   1.0000
   9.000   0.5606   0.09519   0.08418   0.0108   0.2328   1.0000
   9.250   0.5764   0.09663   0.08562   0.0114   0.2307   1.0000
   9.500   0.5795   0.09988   0.08886   0.0107   0.2287   1.0000
   9.750   0.5616   0.10563   0.09465   0.0079   0.2255   1.0000
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