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MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 92 15.49% (mh92-il)
Reynolds number: 50,000
Max Cl/Cd: 15.4 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh92-il-50000.txt
Download as CSV file: xf-mh92-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 92  15.49%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5725   0.10080   0.09442  -0.0064   1.0000   0.1319
 -10.500  -0.5830   0.09232   0.08596  -0.0112   1.0000   0.1230
 -10.250  -0.6744   0.07903   0.07251  -0.0220   1.0000   0.1143
 -10.000  -0.6844   0.07409   0.06754  -0.0225   1.0000   0.1120
  -9.750  -0.7086   0.06951   0.06284  -0.0219   1.0000   0.1097
  -9.500  -0.7387   0.06512   0.05818  -0.0198   1.0000   0.1070
  -9.250  -0.7845   0.06124   0.05348  -0.0154   1.0000   0.1028
  -9.000  -0.7769   0.05727   0.04930  -0.0143   1.0000   0.1018
  -8.750  -0.7699   0.05355   0.04533  -0.0128   1.0000   0.1011
  -8.500  -0.7622   0.05012   0.04159  -0.0111   1.0000   0.1008
  -8.250  -0.7528   0.04711   0.03819  -0.0093   1.0000   0.1012
  -8.000  -0.7436   0.04452   0.03512  -0.0070   1.0000   0.1025
  -7.750  -0.7204   0.04147   0.03221  -0.0069   1.0000   0.1065
  -7.500  -0.7009   0.03914   0.02971  -0.0058   1.0000   0.1102
  -7.250  -0.6815   0.03696   0.02723  -0.0043   1.0000   0.1137
  -7.000  -0.6594   0.03479   0.02510  -0.0035   1.0000   0.1210
  -6.750  -0.6438   0.03336   0.02351  -0.0014   1.0000   0.1291
  -6.500  -0.6235   0.03169   0.02204  -0.0001   1.0000   0.1416
  -6.250  -0.6096   0.03035   0.02082   0.0021   1.0000   0.1587
  -6.000  -0.6010   0.02901   0.01984   0.0049   1.0000   0.1827
  -5.750  -0.6008   0.02771   0.01891   0.0088   1.0000   0.2201
  -5.500  -0.6113   0.02607   0.01807   0.0141   1.0000   0.2916
  -5.250  -0.6310   0.02457   0.01772   0.0214   1.0000   0.4160
  -5.000  -0.6409   0.02432   0.01813   0.0284   1.0000   0.5271
  -4.750  -0.6396   0.02485   0.01894   0.0343   1.0000   0.6015
  -4.500  -0.6321   0.02588   0.02009   0.0395   1.0000   0.6573
  -4.250  -0.5674   0.03001   0.02408   0.0397   0.9858   0.7302
  -4.000  -0.4189   0.03570   0.02914   0.0284   0.9728   0.7810
  -3.750  -0.2580   0.03756   0.03035   0.0094   0.9597   0.8145
  -3.500  -0.1280   0.03734   0.02968  -0.0076   0.9449   0.8435
  -3.250  -0.0216   0.03638   0.02838  -0.0215   0.9281   0.8696
  -3.000   0.0462   0.03557   0.02736  -0.0291   0.9059   0.8922
  -2.750   0.1102   0.03460   0.02618  -0.0357   0.8825   0.9125
  -2.500   0.1573   0.03383   0.02523  -0.0393   0.8595   0.9321
  -2.250   0.1960   0.03319   0.02446  -0.0419   0.8356   0.9514
  -2.000   0.2334   0.03252   0.02366  -0.0443   0.8138   0.9705
  -1.750   0.2797   0.03136   0.02236  -0.0482   0.7922   0.9889
  -1.500   0.3128   0.03064   0.02150  -0.0502   0.7726   1.0000
  -1.250   0.3255   0.03064   0.02142  -0.0487   0.7551   1.0000
  -1.000   0.3389   0.03070   0.02140  -0.0474   0.7381   1.0000
  -0.750   0.3529   0.03082   0.02145  -0.0462   0.7215   1.0000
  -0.500   0.3673   0.03099   0.02155  -0.0450   0.7056   1.0000
  -0.250   0.3819   0.03121   0.02171  -0.0439   0.6904   1.0000
   0.000   0.3962   0.03139   0.02181  -0.0423   0.6770   1.0000
   0.250   0.4106   0.03150   0.02183  -0.0405   0.6642   1.0000
   0.500   0.4267   0.03196   0.02227  -0.0398   0.6493   1.0000
   0.750   0.4425   0.03245   0.02274  -0.0389   0.6359   1.0000
   1.000   0.4574   0.03251   0.02268  -0.0366   0.6255   1.0000
   1.250   0.4736   0.03312   0.02330  -0.0360   0.6116   1.0000
   1.500   0.4892   0.03391   0.02410  -0.0353   0.5987   1.0000
   1.750   0.5055   0.03383   0.02389  -0.0327   0.5902   1.0000
   2.000   0.5202   0.03500   0.02512  -0.0326   0.5764   1.0000
   2.250   0.5345   0.03598   0.02613  -0.0318   0.5652   1.0000
   2.500   0.5510   0.03622   0.02630  -0.0297   0.5560   1.0000
   2.750   0.5617   0.03782   0.02798  -0.0293   0.5438   1.0000
   3.000   0.5806   0.03769   0.02774  -0.0268   0.5367   1.0000
   3.250   0.5849   0.04010   0.03031  -0.0266   0.5244   1.0000
   3.500   0.6023   0.04034   0.03047  -0.0244   0.5170   1.0000
   3.750   0.6013   0.04297   0.03322  -0.0236   0.5060   1.0000
   4.000   0.6174   0.04345   0.03366  -0.0214   0.4992   1.0000
   4.250   0.5995   0.04738   0.03771  -0.0201   0.4890   1.0000
   4.500   0.6333   0.04616   0.03639  -0.0175   0.4832   1.0000
   4.750   0.5608   0.05410   0.04447  -0.0151   0.4750   1.0000
   5.000   0.5562   0.05614   0.04649  -0.0125   0.4691   1.0000
   5.250   0.5510   0.05828   0.04859  -0.0098   0.4636   1.0000
   5.500   0.4812   0.06347   0.05367  -0.0046   0.4627   1.0000
   5.750   0.4415   0.06706   0.05715  -0.0009   0.4618   1.0000
   6.000   0.4209   0.07034   0.06036   0.0011   0.4619   1.0000
   6.250   0.4122   0.07345   0.06343   0.0021   0.4630   1.0000
   6.500   0.4103   0.07652   0.06648   0.0026   0.4642   1.0000
   7.750   0.3253   0.09483   0.08473  -0.0002   0.5434   1.0000
   8.000   0.3622   0.09944   0.08937  -0.0019   0.5365   1.0000
   8.250   0.3439   0.09946   0.08935   0.0001   0.5254   1.0000
   8.500   0.3784   0.10410   0.09402  -0.0013   0.5180   1.0000
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