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MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 80 12.72% (mh80-il)
Reynolds number: 50,000
Max Cl/Cd: 12.29 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh80-il-50000.txt
Download as CSV file: xf-mh80-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 80  12.72%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4461   0.11242   0.10695   0.0228   1.0000   0.2423
  -8.500  -0.4215   0.10714   0.10171   0.0236   1.0000   0.2506
  -8.250  -0.4485   0.10631   0.10108   0.0197   1.0000   0.2605
  -8.000  -0.4223   0.10147   0.09626   0.0211   1.0000   0.2755
  -7.750  -0.4034   0.09712   0.09199   0.0215   1.0000   0.2885
  -7.500  -0.3953   0.09361   0.08858   0.0211   1.0000   0.3026
  -7.250  -0.3903   0.09032   0.08542   0.0203   1.0000   0.3171
  -7.000  -0.3830   0.08697   0.08219   0.0199   1.0000   0.3340
  -6.000  -0.4428   0.05854   0.05331  -0.0185   1.0000   0.1426
  -5.750  -0.4599   0.05771   0.05261  -0.0149   1.0000   0.1407
  -5.500  -0.4324   0.05114   0.04547  -0.0208   0.9809   0.1234
  -5.250  -0.3844   0.04421   0.03744  -0.0280   0.9592   0.1119
  -5.000  -0.3348   0.03948   0.03213  -0.0330   0.9359   0.1090
  -4.750  -0.2888   0.03599   0.02797  -0.0361   0.9128   0.1098
  -4.500  -0.2566   0.03381   0.02516  -0.0362   0.8873   0.1146
  -4.250  -0.2263   0.03200   0.02326  -0.0356   0.8645   0.1220
  -4.000  -0.2012   0.03062   0.02159  -0.0341   0.8411   0.1320
  -3.750  -0.1760   0.02934   0.02026  -0.0323   0.8201   0.1502
  -3.500  -0.1507   0.02806   0.01905  -0.0304   0.8009   0.1833
  -3.250  -0.1264   0.02619   0.01768  -0.0284   0.7832   0.2748
  -3.000  -0.1189   0.02366   0.01690  -0.0237   0.7676   0.5020
  -2.750   0.0852   0.02400   0.01719  -0.0389   0.7321   1.0000
  -2.500   0.0995   0.02397   0.01683  -0.0381   0.7156   1.0000
  -2.250   0.1167   0.02408   0.01664  -0.0374   0.6995   1.0000
  -2.000   0.1349   0.02430   0.01658  -0.0366   0.6839   1.0000
  -1.750   0.1546   0.02460   0.01662  -0.0360   0.6690   1.0000
  -1.500   0.1746   0.02499   0.01677  -0.0353   0.6551   1.0000
  -1.250   0.1940   0.02539   0.01693  -0.0343   0.6425   1.0000
  -1.000   0.2128   0.02576   0.01704  -0.0328   0.6309   1.0000
  -0.750   0.2350   0.02641   0.01755  -0.0328   0.6176   1.0000
  -0.500   0.2559   0.02706   0.01803  -0.0322   0.6062   1.0000
  -0.250   0.2751   0.02750   0.01824  -0.0305   0.5966   1.0000
   0.000   0.2974   0.02845   0.01911  -0.0309   0.5845   1.0000
   0.250   0.3172   0.02910   0.01959  -0.0297   0.5758   1.0000
   0.500   0.3382   0.03007   0.02047  -0.0296   0.5652   1.0000
   0.750   0.3583   0.03109   0.02140  -0.0292   0.5561   1.0000
   1.000   0.3780   0.03200   0.02220  -0.0284   0.5474   1.0000
   1.250   0.3971   0.03337   0.02352  -0.0284   0.5390   1.0000
   1.500   0.4158   0.03447   0.02455  -0.0278   0.5308   1.0000
   1.750   0.4333   0.03586   0.02588  -0.0273   0.5233   1.0000
   2.000   0.4488   0.03769   0.02771  -0.0276   0.5153   1.0000
   2.250   0.4693   0.03820   0.02806  -0.0254   0.5102   1.0000
   2.500   0.4745   0.04175   0.03174  -0.0276   0.5019   1.0000
   2.750   0.4907   0.04302   0.03293  -0.0265   0.4958   1.0000
   3.000   0.5011   0.04525   0.03514  -0.0262   0.4906   1.0000
   3.250   0.4918   0.04969   0.03964  -0.0279   0.4866   1.0000
   3.500   0.4874   0.05308   0.04302  -0.0283   0.4831   1.0000
   3.750   0.4930   0.05555   0.04544  -0.0279   0.4797   1.0000
   4.000   0.5150   0.05687   0.04668  -0.0265   0.4754   1.0000
   4.250   0.5100   0.06070   0.05051  -0.0273   0.4762   1.0000
   5.000   0.3491   0.07786   0.06770  -0.0345   0.6186   1.0000
   5.250   0.3694   0.08077   0.07057  -0.0349   0.6107   1.0000
   5.500   0.3849   0.08276   0.07251  -0.0346   0.5975   1.0000
   5.750   0.3856   0.08420   0.07390  -0.0334   0.5854   1.0000
   6.000   0.4247   0.08865   0.07833  -0.0351   0.5783   1.0000
   6.250   0.4119   0.08881   0.07844  -0.0331   0.5659   1.0000
   6.500   0.4300   0.09192   0.08153  -0.0334   0.5591   1.0000
   6.750   0.4415   0.09380   0.08339  -0.0330   0.5466   1.0000
   7.000   0.4424   0.09557   0.08514  -0.0323   0.5364   1.0000
   7.250   0.4703   0.09908   0.08864  -0.0330   0.5282   1.0000
   7.500   0.4633   0.10033   0.08987  -0.0322   0.5191   1.0000
   7.750   0.4910   0.10397   0.09351  -0.0329   0.5112   1.0000
   8.000   0.4841   0.10519   0.09471  -0.0321   0.5011   1.0000
   8.250   0.5168   0.10946   0.09902  -0.0330   0.4936   1.0000
   8.500   0.5044   0.11017   0.09969  -0.0322   0.4836   1.0000
   8.750   0.5321   0.11419   0.10376  -0.0329   0.4772   1.0000
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