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MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 93 15.98% (mh93-il)
Reynolds number: 50,000
Max Cl/Cd: 14.62 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh93-il-50000.txt
Download as CSV file: xf-mh93-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 93  15.98%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6131   0.10080   0.09437  -0.0108   1.0000   0.1254
 -11.000  -0.5925   0.09740   0.09099  -0.0095   1.0000   0.1229
 -10.750  -0.6879   0.08231   0.07578  -0.0214   1.0000   0.1129
 -10.500  -0.7098   0.07706   0.07040  -0.0224   1.0000   0.1104
 -10.250  -0.7223   0.07246   0.06573  -0.0223   1.0000   0.1087
 -10.000  -0.7433   0.06826   0.06139  -0.0209   1.0000   0.1069
  -9.750  -0.7652   0.06428   0.05718  -0.0187   1.0000   0.1050
  -9.500  -0.7835   0.06019   0.05273  -0.0161   1.0000   0.1029
  -9.250  -0.8005   0.05633   0.04830  -0.0129   1.0000   0.1007
  -9.000  -0.8066   0.05333   0.04470  -0.0097   1.0000   0.0994
  -8.750  -0.7943   0.04974   0.04091  -0.0085   1.0000   0.1002
  -8.500  -0.7739   0.04682   0.03801  -0.0080   1.0000   0.1032
  -8.250  -0.7589   0.04423   0.03520  -0.0067   1.0000   0.1058
  -8.000  -0.7433   0.04171   0.03235  -0.0052   1.0000   0.1086
  -7.750  -0.7264   0.03934   0.02954  -0.0035   1.0000   0.1115
  -7.500  -0.6980   0.03679   0.02715  -0.0038   1.0000   0.1176
  -7.250  -0.6800   0.03514   0.02522  -0.0022   1.0000   0.1255
  -7.000  -0.6526   0.03313   0.02343  -0.0020   1.0000   0.1380
  -6.750  -0.6339   0.03160   0.02204  -0.0005   1.0000   0.1542
  -6.500  -0.6210   0.03016   0.02098   0.0017   1.0000   0.1769
  -6.250  -0.6207   0.02897   0.02011   0.0056   1.0000   0.2073
  -6.000  -0.6290   0.02775   0.01935   0.0106   1.0000   0.2520
  -5.750  -0.6468   0.02634   0.01880   0.0170   1.0000   0.3260
  -5.500  -0.6673   0.02527   0.01866   0.0247   1.0000   0.4363
  -5.250  -0.6762   0.02518   0.01906   0.0314   1.0000   0.5281
  -5.000  -0.6741   0.02577   0.01991   0.0371   1.0000   0.5963
  -4.750  -0.6424   0.02796   0.02218   0.0398   0.9935   0.6647
  -4.500  -0.5184   0.03499   0.02882   0.0344   0.9794   0.7339
  -4.250  -0.3414   0.03923   0.03231   0.0166   0.9678   0.7719
  -4.000  -0.2308   0.03971   0.03235   0.0035   0.9526   0.8026
  -3.750  -0.1004   0.03918   0.03140  -0.0133   0.9379   0.8292
  -3.500  -0.0260   0.03843   0.03039  -0.0220   0.9188   0.8538
  -3.250   0.0444   0.03751   0.02924  -0.0296   0.8979   0.8748
  -3.000   0.0955   0.03678   0.02833  -0.0338   0.8759   0.8944
  -2.750   0.1340   0.03622   0.02763  -0.0361   0.8528   0.9133
  -2.500   0.1711   0.03560   0.02687  -0.0382   0.8314   0.9321
  -2.250   0.2069   0.03494   0.02609  -0.0401   0.8111   0.9505
  -2.000   0.2427   0.03428   0.02529  -0.0423   0.7918   0.9692
  -1.750   0.2873   0.03314   0.02402  -0.0461   0.7720   0.9872
  -1.500   0.3243   0.03227   0.02303  -0.0488   0.7534   1.0000
  -1.250   0.3381   0.03230   0.02300  -0.0478   0.7369   1.0000
  -1.000   0.3523   0.03239   0.02302  -0.0469   0.7210   1.0000
  -0.750   0.3669   0.03255   0.02312  -0.0460   0.7061   1.0000
  -0.500   0.3808   0.03268   0.02318  -0.0446   0.6924   1.0000
  -0.250   0.3942   0.03272   0.02311  -0.0427   0.6800   1.0000
   0.000   0.4104   0.03310   0.02348  -0.0423   0.6651   1.0000
   0.250   0.4260   0.03350   0.02384  -0.0414   0.6518   1.0000
   0.500   0.4398   0.03348   0.02370  -0.0390   0.6420   1.0000
   0.750   0.4563   0.03413   0.02436  -0.0388   0.6274   1.0000
   1.000   0.4720   0.03477   0.02500  -0.0382   0.6151   1.0000
   1.250   0.4872   0.03480   0.02493  -0.0359   0.6058   1.0000
   1.500   0.5026   0.03583   0.02600  -0.0359   0.5922   1.0000
   1.750   0.5178   0.03642   0.02657  -0.0346   0.5822   1.0000
   2.000   0.5329   0.03705   0.02718  -0.0334   0.5715   1.0000
   2.250   0.5458   0.03829   0.02847  -0.0328   0.5600   1.0000
   2.500   0.5622   0.03846   0.02857  -0.0307   0.5518   1.0000
   2.750   0.5707   0.04045   0.03065  -0.0307   0.5401   1.0000
   3.000   0.5892   0.04031   0.03042  -0.0281   0.5329   1.0000
   3.250   0.5897   0.04315   0.03342  -0.0281   0.5212   1.0000
   3.500   0.6103   0.04288   0.03306  -0.0256   0.5148   1.0000
   3.750   0.5970   0.04690   0.03723  -0.0252   0.5036   1.0000
   4.000   0.6197   0.04656   0.03683  -0.0228   0.4974   1.0000
   4.250   0.5819   0.05227   0.04265  -0.0214   0.4883   1.0000
   4.500   0.5853   0.05375   0.04413  -0.0191   0.4816   1.0000
   4.750   0.5728   0.05653   0.04689  -0.0166   0.4757   1.0000
   5.000   0.4956   0.06259   0.05290  -0.0116   0.4731   1.0000
   5.250   0.4472   0.06592   0.05614  -0.0062   0.4725   1.0000
   5.500   0.4166   0.06890   0.05905  -0.0026   0.4726   1.0000
   5.750   0.3965   0.07172   0.06180  -0.0001   0.4735   1.0000
   6.000   0.3856   0.07449   0.06452   0.0016   0.4750   1.0000
   6.250   0.3810   0.07747   0.06750   0.0024   0.4796   1.0000
   6.500   0.2673   0.08579   0.07577   0.0006   0.5901   1.0000
   6.750   0.2774   0.08833   0.07828   0.0010   0.5842   1.0000
   7.000   0.2854   0.08984   0.07976   0.0020   0.5714   1.0000
   7.250   0.2867   0.09169   0.08159   0.0030   0.5631   1.0000
   7.500   0.3039   0.09408   0.08398   0.0030   0.5529   1.0000
   7.750   0.3063   0.09617   0.08605   0.0037   0.5462   1.0000
   8.000   0.3219   0.09844   0.08832   0.0038   0.5347   1.0000
   8.250   0.3214   0.10024   0.09010   0.0046   0.5263   1.0000
   8.500   0.3421   0.10308   0.09295   0.0043   0.5163   1.0000
   8.750   0.3411   0.10504   0.09489   0.0048   0.5097   1.0000
   9.000   0.3579   0.10760   0.09748   0.0047   0.4988   1.0000
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