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MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 62 9.3% (mh62-il)
Reynolds number: 100,000
Max Cl/Cd: 44.97 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh62-il-100000.txt
Download as CSV file: xf-mh62-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 62  9.3%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5351   0.09690   0.09259   0.0064   1.0000   0.1083
  -8.250  -0.5342   0.09331   0.08906   0.0040   1.0000   0.1130
  -8.000  -0.5717   0.08890   0.08479  -0.0095   1.0000   0.1164
  -7.750  -0.5387   0.08498   0.08088  -0.0015   1.0000   0.1203
  -7.500  -0.5372   0.08125   0.07721  -0.0035   1.0000   0.1257
  -7.250  -0.5498   0.07544   0.07143  -0.0126   1.0000   0.1319
  -7.000  -0.5333   0.07228   0.06827  -0.0106   1.0000   0.1364
  -6.750  -0.5353   0.06700   0.06293  -0.0167   1.0000   0.1462
  -6.500  -0.5211   0.06341   0.05935  -0.0168   1.0000   0.1512
  -6.250  -0.5240   0.04322   0.03768  -0.0291   1.0000   0.0611
  -6.000  -0.5072   0.03738   0.03097  -0.0285   1.0000   0.0497
  -5.750  -0.4891   0.03317   0.02643  -0.0280   1.0000   0.0472
  -5.500  -0.4696   0.02973   0.02251  -0.0271   1.0000   0.0452
  -5.250  -0.4506   0.02697   0.01924  -0.0255   1.0000   0.0442
  -5.000  -0.4342   0.02489   0.01682  -0.0234   1.0000   0.0442
  -4.750  -0.4188   0.02318   0.01488  -0.0212   1.0000   0.0453
  -4.500  -0.4032   0.02199   0.01347  -0.0190   1.0000   0.0491
  -4.250  -0.3878   0.02039   0.01183  -0.0170   1.0000   0.0540
  -4.000  -0.3715   0.01918   0.01059  -0.0150   1.0000   0.0611
  -3.750  -0.3560   0.01787   0.00933  -0.0130   1.0000   0.0775
  -3.500  -0.3414   0.01614   0.00810  -0.0110   1.0000   0.1417
  -3.250  -0.3281   0.01469   0.00770  -0.0092   1.0000   0.3333
  -3.000  -0.2910   0.01427   0.00761  -0.0115   0.9909   0.4528
  -2.750  -0.2513   0.01388   0.00759  -0.0139   0.9817   0.5631
  -2.500  -0.2142   0.01345   0.00754  -0.0152   0.9720   0.6720
  -2.250  -0.1725   0.01311   0.00757  -0.0165   0.9643   0.8041
  -2.000  -0.0794   0.01309   0.00746  -0.0272   0.9657   0.9453
  -1.750   0.0208   0.01297   0.00696  -0.0411   0.9676   1.0000
  -1.500   0.0721   0.01288   0.00661  -0.0465   0.9559   1.0000
  -1.250   0.1154   0.01285   0.00639  -0.0500   0.9422   1.0000
  -1.000   0.1495   0.01290   0.00629  -0.0515   0.9267   1.0000
  -0.750   0.1756   0.01303   0.00627  -0.0512   0.9101   1.0000
  -0.500   0.1977   0.01320   0.00633  -0.0500   0.8939   1.0000
  -0.250   0.2176   0.01338   0.00641  -0.0482   0.8780   1.0000
   0.000   0.2364   0.01357   0.00650  -0.0461   0.8627   1.0000
   0.250   0.2550   0.01375   0.00658  -0.0438   0.8477   1.0000
   0.500   0.2737   0.01391   0.00666  -0.0415   0.8330   1.0000
   0.750   0.2928   0.01405   0.00672  -0.0393   0.8184   1.0000
   1.000   0.3128   0.01420   0.00680  -0.0373   0.8029   1.0000
   1.250   0.3334   0.01433   0.00688  -0.0354   0.7872   1.0000
   1.500   0.3543   0.01443   0.00694  -0.0335   0.7714   1.0000
   1.750   0.3755   0.01451   0.00697  -0.0316   0.7556   1.0000
   2.000   0.3972   0.01457   0.00697  -0.0298   0.7398   1.0000
   2.250   0.4193   0.01460   0.00696  -0.0280   0.7239   1.0000
   2.500   0.4418   0.01462   0.00694  -0.0262   0.7079   1.0000
   2.750   0.4651   0.01467   0.00698  -0.0248   0.6895   1.0000
   3.000   0.4886   0.01470   0.00698  -0.0234   0.6708   1.0000
   3.250   0.5122   0.01469   0.00692  -0.0218   0.6529   1.0000
   3.500   0.5365   0.01476   0.00700  -0.0207   0.6318   1.0000
   3.750   0.5607   0.01478   0.00698  -0.0193   0.6116   1.0000
   4.000   0.5853   0.01489   0.00707  -0.0183   0.5885   1.0000
   4.250   0.6099   0.01499   0.00712  -0.0171   0.5658   1.0000
   4.500   0.6345   0.01514   0.00725  -0.0161   0.5418   1.0000
   4.750   0.6592   0.01537   0.00744  -0.0152   0.5158   1.0000
   5.000   0.6838   0.01565   0.00768  -0.0143   0.4894   1.0000
   5.250   0.7083   0.01598   0.00797  -0.0135   0.4623   1.0000
   5.500   0.7327   0.01639   0.00833  -0.0127   0.4347   1.0000
   5.750   0.7568   0.01684   0.00877  -0.0119   0.4066   1.0000
   6.000   0.7807   0.01736   0.00924  -0.0112   0.3785   1.0000
   6.250   0.8042   0.01793   0.00976  -0.0105   0.3501   1.0000
   6.500   0.8275   0.01857   0.01035  -0.0097   0.3219   1.0000
   6.750   0.8504   0.01926   0.01101  -0.0090   0.2943   1.0000
   7.000   0.8728   0.02001   0.01173  -0.0083   0.2672   1.0000
   7.250   0.8948   0.02084   0.01261  -0.0076   0.2412   1.0000
   7.500   0.9162   0.02173   0.01350  -0.0068   0.2159   1.0000
   7.750   0.9369   0.02273   0.01445  -0.0060   0.1922   1.0000
   8.000   0.9567   0.02380   0.01542  -0.0052   0.1689   1.0000
   8.250   0.9753   0.02493   0.01664  -0.0042   0.1448   1.0000
   8.500   0.9927   0.02634   0.01809  -0.0032   0.1224   1.0000
   8.750   1.0087   0.02793   0.01949  -0.0022   0.1023   1.0000
   9.000   1.0248   0.02984   0.02159  -0.0008   0.0857   1.0000
   9.250   1.0396   0.03170   0.02354   0.0004   0.0722   1.0000
   9.500   1.0563   0.03436   0.02626   0.0016   0.0630   1.0000
   9.750   1.0695   0.03620   0.02831   0.0029   0.0548   1.0000
  10.000   1.0812   0.03956   0.03198   0.0043   0.0493   1.0000
  10.250   1.0903   0.04197   0.03466   0.0058   0.0443   1.0000
  10.500   1.0953   0.04568   0.03848   0.0069   0.0403   1.0000
  10.750   1.0925   0.04892   0.04222   0.0089   0.0386   1.0000
  11.000   1.0847   0.05248   0.04616   0.0107   0.0380   1.0000
  11.250   1.0698   0.05608   0.05007   0.0124   0.0375   1.0000
  11.500   1.0537   0.06000   0.05426   0.0129   0.0375   1.0000
  11.750   1.0359   0.06446   0.05896   0.0121   0.0376   1.0000
  12.000   1.0152   0.06969   0.06441   0.0102   0.0379   1.0000
  12.250   0.9950   0.07544   0.07035   0.0072   0.0383   1.0000
  12.500   0.9749   0.08186   0.07692   0.0033   0.0389   1.0000
  12.750   0.9517   0.08953   0.08472  -0.0018   0.0394   1.0000
  13.000   0.9298   0.09785   0.09312  -0.0073   0.0401   1.0000
  13.250   0.9149   0.10547   0.10077  -0.0115   0.0408   1.0000
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