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MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 61 10.26% (mh61-il)
Reynolds number: 50,000
Max Cl/Cd: 32.97 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh61-il-50000-n5.txt
Download as CSV file: xf-mh61-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 61  10.26%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5610   0.09825   0.09218   0.0007   1.0000   0.0326
  -9.250  -0.5634   0.09255   0.08655  -0.0030   1.0000   0.0319
  -9.000  -0.5676   0.08611   0.08019  -0.0078   1.0000   0.0311
  -8.750  -0.5762   0.07824   0.07235  -0.0147   1.0000   0.0302
  -8.500  -0.5938   0.07135   0.06542  -0.0208   1.0000   0.0292
  -8.250  -0.6084   0.06578   0.05963  -0.0240   1.0000   0.0285
  -8.000  -0.6129   0.06109   0.05466  -0.0256   1.0000   0.0281
  -7.750  -0.6113   0.05688   0.05012  -0.0264   1.0000   0.0278
  -7.500  -0.6057   0.05285   0.04573  -0.0268   1.0000   0.0277
  -7.250  -0.5964   0.04903   0.04151  -0.0268   1.0000   0.0276
  -7.000  -0.5850   0.04518   0.03727  -0.0267   1.0000   0.0278
  -6.750  -0.5705   0.04167   0.03338  -0.0263   1.0000   0.0281
  -6.500  -0.5541   0.03847   0.02972  -0.0258   1.0000   0.0287
  -6.250  -0.5362   0.03576   0.02671  -0.0251   1.0000   0.0297
  -6.000  -0.5183   0.03367   0.02437  -0.0242   1.0000   0.0317
  -5.750  -0.5016   0.03189   0.02231  -0.0228   1.0000   0.0354
  -5.500  -0.4865   0.03038   0.02047  -0.0207   1.0000   0.0380
  -5.250  -0.4747   0.02867   0.01867  -0.0183   1.0000   0.0407
  -5.000  -0.4637   0.02732   0.01722  -0.0157   1.0000   0.0439
  -4.750  -0.4325   0.02563   0.01531  -0.0168   0.9885   0.0539
  -4.500  -0.3991   0.02377   0.01339  -0.0183   0.9785   0.0777
  -4.250  -0.3678   0.02097   0.01179  -0.0206   0.9698   0.2385
  -4.000  -0.3422   0.02005   0.01158  -0.0209   0.9588   0.4096
  -3.750  -0.3144   0.01966   0.01125  -0.0208   0.9487   0.5005
  -3.500  -0.2832   0.01932   0.01091  -0.0210   0.9397   0.5643
  -3.250  -0.2521   0.01905   0.01062  -0.0211   0.9307   0.6228
  -3.000  -0.2217   0.01883   0.01040  -0.0209   0.9215   0.6806
  -2.750  -0.1851   0.01869   0.01023  -0.0215   0.9140   0.7418
  -2.500  -0.1438   0.01865   0.01004  -0.0231   0.9061   0.8025
  -2.250  -0.0916   0.01869   0.00987  -0.0268   0.8999   0.8572
  -2.000  -0.0381   0.01875   0.00967  -0.0312   0.8926   0.9019
  -1.750   0.0172   0.01878   0.00937  -0.0362   0.8853   0.9382
  -1.500   0.0701   0.01875   0.00910  -0.0412   0.8771   0.9705
  -1.250   0.1244   0.01860   0.00873  -0.0470   0.8685   1.0000
  -1.000   0.1428   0.01871   0.00865  -0.0459   0.8563   1.0000
  -0.750   0.1617   0.01886   0.00865  -0.0448   0.8447   1.0000
  -0.500   0.1811   0.01901   0.00867  -0.0435   0.8337   1.0000
  -0.250   0.2007   0.01921   0.00875  -0.0423   0.8222   1.0000
   0.000   0.2207   0.01942   0.00886  -0.0412   0.8106   1.0000
   0.250   0.2410   0.01964   0.00899  -0.0400   0.7993   1.0000
   0.500   0.2616   0.01986   0.00913  -0.0388   0.7884   1.0000
   0.750   0.2826   0.02006   0.00926  -0.0375   0.7780   1.0000
   1.000   0.3037   0.02027   0.00942  -0.0362   0.7672   1.0000
   1.250   0.3250   0.02052   0.00964  -0.0351   0.7555   1.0000
   1.500   0.3466   0.02076   0.00989  -0.0340   0.7440   1.0000
   1.750   0.3683   0.02100   0.01011  -0.0329   0.7327   1.0000
   2.000   0.3903   0.02121   0.01031  -0.0316   0.7217   1.0000
   2.250   0.4124   0.02136   0.01047  -0.0302   0.7113   1.0000
   2.500   0.4345   0.02160   0.01079  -0.0291   0.6991   1.0000
   2.750   0.4566   0.02184   0.01107  -0.0280   0.6867   1.0000
   3.000   0.4789   0.02207   0.01137  -0.0268   0.6741   1.0000
   3.250   0.5013   0.02228   0.01165  -0.0256   0.6615   1.0000
   3.500   0.5238   0.02249   0.01194  -0.0245   0.6486   1.0000
   3.750   0.5464   0.02268   0.01227  -0.0232   0.6354   1.0000
   4.000   0.5692   0.02286   0.01255  -0.0220   0.6219   1.0000
   4.250   0.5921   0.02303   0.01284  -0.0208   0.6080   1.0000
   4.500   0.6151   0.02318   0.01312  -0.0195   0.5936   1.0000
   4.750   0.6382   0.02331   0.01338  -0.0182   0.5786   1.0000
   5.000   0.6614   0.02340   0.01367  -0.0168   0.5632   1.0000
   5.250   0.6842   0.02358   0.01400  -0.0155   0.5457   1.0000
   5.500   0.7068   0.02375   0.01434  -0.0142   0.5264   1.0000
   5.750   0.7300   0.02376   0.01447  -0.0126   0.5071   1.0000
   6.000   0.7519   0.02398   0.01485  -0.0112   0.4834   1.0000
   6.250   0.7735   0.02417   0.01518  -0.0097   0.4577   1.0000
   6.500   0.7945   0.02439   0.01561  -0.0081   0.4288   1.0000
   6.750   0.8141   0.02473   0.01602  -0.0065   0.3955   1.0000
   7.000   0.8319   0.02523   0.01652  -0.0048   0.3569   1.0000
   7.250   0.8471   0.02600   0.01729  -0.0032   0.3112   1.0000
   7.500   0.8589   0.02708   0.01823  -0.0014   0.2594   1.0000
   7.750   0.8668   0.02862   0.01952   0.0003   0.2040   1.0000
   8.000   0.8714   0.03059   0.02116   0.0020   0.1564   1.0000
   8.250   0.8752   0.03278   0.02312   0.0037   0.1231   1.0000
   8.500   0.8776   0.03508   0.02522   0.0055   0.0990   1.0000
   8.750   0.8807   0.03728   0.02736   0.0072   0.0813   1.0000
   9.000   0.8844   0.03954   0.02965   0.0092   0.0706   1.0000
   9.250   0.8886   0.04179   0.03190   0.0107   0.0610   1.0000
   9.500   0.8923   0.04405   0.03416   0.0119   0.0529   1.0000
   9.750   0.9084   0.04644   0.03685   0.0137   0.0466   1.0000
  10.000   0.9177   0.04886   0.03947   0.0149   0.0418   1.0000
  10.250   0.9255   0.05169   0.04254   0.0159   0.0376   1.0000
  10.500   0.9304   0.05465   0.04583   0.0167   0.0346   1.0000
  10.750   0.9334   0.05799   0.04945   0.0174   0.0328   1.0000
  11.000   0.9325   0.06157   0.05325   0.0176   0.0317   1.0000
  11.250   0.9282   0.06547   0.05738   0.0175   0.0309   1.0000
  11.500   0.9211   0.06970   0.06182   0.0167   0.0305   1.0000
  11.750   0.9112   0.07437   0.06669   0.0154   0.0302   1.0000
  12.000   0.8979   0.07967   0.07221   0.0132   0.0301   1.0000
  12.250   0.8821   0.08565   0.07838   0.0102   0.0302   1.0000
  12.500   0.8605   0.09327   0.08624   0.0055   0.0308   1.0000
  12.750   0.8367   0.10239   0.09553  -0.0004   0.0316   1.0000
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