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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 50,000
Max Cl/Cd: 35 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh22-il-50000-n5.txt
Download as CSV file: xf-mh22-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 22  7.2%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4548   0.10683   0.10055   0.0007   1.0000   0.0388
  -9.000  -0.4481   0.10250   0.09624   0.0007   1.0000   0.0373
  -8.750  -0.5254   0.10469   0.09804   0.0032   1.0000   0.0374
  -8.500  -0.5212   0.10067   0.09407   0.0019   1.0000   0.0361
  -8.250  -0.5182   0.09673   0.09020   0.0001   1.0000   0.0349
  -8.000  -0.5168   0.09258   0.08614  -0.0020   1.0000   0.0339
  -7.750  -0.5161   0.08853   0.08217  -0.0045   1.0000   0.0330
  -7.500  -0.5162   0.08432   0.07804  -0.0075   1.0000   0.0320
  -7.250  -0.5137   0.07947   0.07324  -0.0114   1.0000   0.0311
  -7.000  -0.5098   0.07411   0.06789  -0.0157   1.0000   0.0300
  -6.750  -0.5038   0.06804   0.06175  -0.0203   1.0000   0.0287
  -6.250  -0.4828   0.05783   0.05106  -0.0255   1.0000   0.0272
  -6.000  -0.4712   0.05338   0.04640  -0.0266   1.0000   0.0270
  -5.750  -0.4576   0.04895   0.04167  -0.0274   1.0000   0.0269
  -5.500  -0.4419   0.04471   0.03705  -0.0279   1.0000   0.0269
  -5.250  -0.4242   0.04071   0.03258  -0.0278   1.0000   0.0270
  -5.000  -0.4045   0.03709   0.02845  -0.0275   1.0000   0.0272
  -4.750  -0.3846   0.03352   0.02449  -0.0270   1.0000   0.0282
  -4.500  -0.3638   0.03124   0.02199  -0.0265   1.0000   0.0322
  -4.250  -0.3399   0.02891   0.01895  -0.0257   1.0000   0.0373
  -4.000  -0.3153   0.02645   0.01607  -0.0246   1.0000   0.0406
  -3.750  -0.2916   0.02439   0.01386  -0.0235   1.0000   0.0454
  -3.500  -0.2674   0.02267   0.01197  -0.0224   1.0000   0.0572
  -3.250  -0.2425   0.02107   0.01034  -0.0217   1.0000   0.0882
  -3.000  -0.2194   0.01955   0.00908  -0.0210   1.0000   0.1524
  -2.750  -0.1988   0.01828   0.00823  -0.0201   1.0000   0.2415
  -2.500  -0.1810   0.01705   0.00761  -0.0187   1.0000   0.3699
  -2.250  -0.1691   0.01561   0.00733  -0.0154   1.0000   0.6099
  -2.000  -0.0738   0.01473   0.00638  -0.0262   1.0000   1.0000
  -1.750  -0.0606   0.01482   0.00607  -0.0242   1.0000   1.0000
  -1.500  -0.0494   0.01498   0.00598  -0.0220   1.0000   1.0000
  -1.250  -0.0192   0.01516   0.00583  -0.0235   0.9879   1.0000
  -1.000   0.0250   0.01532   0.00566  -0.0273   0.9701   1.0000
  -0.750   0.0699   0.01546   0.00552  -0.0312   0.9543   1.0000
  -0.500   0.1112   0.01559   0.00534  -0.0342   0.9372   1.0000
  -0.250   0.1511   0.01573   0.00530  -0.0368   0.9204   1.0000
   0.000   0.1892   0.01587   0.00529  -0.0389   0.9039   1.0000
   0.250   0.2237   0.01602   0.00533  -0.0401   0.8871   1.0000
   0.500   0.2541   0.01620   0.00542  -0.0406   0.8695   1.0000
   0.750   0.2830   0.01640   0.00556  -0.0406   0.8527   1.0000
   1.000   0.3105   0.01660   0.00569  -0.0403   0.8364   1.0000
   1.250   0.3358   0.01683   0.00588  -0.0395   0.8196   1.0000
   1.500   0.3604   0.01707   0.00609  -0.0386   0.8029   1.0000
   1.750   0.3847   0.01732   0.00632  -0.0376   0.7865   1.0000
   2.000   0.4089   0.01756   0.00657  -0.0365   0.7706   1.0000
   2.250   0.4326   0.01782   0.00694  -0.0354   0.7537   1.0000
   2.500   0.4561   0.01808   0.00725  -0.0342   0.7363   1.0000
   2.750   0.4798   0.01833   0.00755  -0.0330   0.7193   1.0000
   3.000   0.5034   0.01859   0.00787  -0.0318   0.7019   1.0000
   3.250   0.5268   0.01886   0.00825  -0.0306   0.6828   1.0000
   3.500   0.5504   0.01911   0.00858  -0.0293   0.6645   1.0000
   3.750   0.5739   0.01939   0.00918  -0.0281   0.6435   1.0000
   4.000   0.5977   0.01963   0.00955  -0.0268   0.6229   1.0000
   4.250   0.6212   0.01989   0.00999  -0.0255   0.5997   1.0000
   4.500   0.6446   0.02013   0.01042  -0.0242   0.5746   1.0000
   4.750   0.6678   0.02036   0.01084  -0.0228   0.5477   1.0000
   5.000   0.6908   0.02056   0.01120  -0.0212   0.5186   1.0000
   5.250   0.7133   0.02083   0.01167  -0.0197   0.4843   1.0000
   5.500   0.7352   0.02114   0.01209  -0.0180   0.4457   1.0000
   5.750   0.7553   0.02158   0.01280  -0.0161   0.3946   1.0000
   6.000   0.7716   0.02232   0.01333  -0.0140   0.3118   1.0000
   6.250   0.7823   0.02421   0.01440  -0.0123   0.1691   1.0000
   6.500   0.7898   0.02769   0.01696  -0.0107   0.0756   1.0000
   6.750   0.8013   0.03041   0.01945  -0.0092   0.0482   1.0000
   7.000   0.8164   0.03278   0.02203  -0.0071   0.0396   1.0000
   7.250   0.8323   0.03515   0.02454  -0.0055   0.0326   1.0000
   7.500   0.8472   0.03737   0.02689  -0.0044   0.0255   1.0000
   7.750   0.8653   0.04034   0.03011  -0.0029   0.0236   1.0000
   8.000   0.8840   0.04344   0.03367  -0.0015   0.0225   1.0000
   8.250   0.8986   0.04691   0.03761  -0.0002   0.0218   1.0000
   8.500   0.9083   0.05064   0.04181   0.0010   0.0214   1.0000
   8.750   0.9127   0.05458   0.04619   0.0021   0.0212   1.0000
   9.000   0.9118   0.05860   0.05060   0.0030   0.0211   1.0000
   9.250   0.9061   0.06258   0.05489   0.0036   0.0211   1.0000
   9.500   0.8940   0.06651   0.05906   0.0040   0.0212   1.0000
   9.750   0.8796   0.07069   0.06342   0.0033   0.0213   1.0000
  10.000   0.8653   0.07543   0.06830   0.0010   0.0215   1.0000
  10.250   0.8507   0.08091   0.07391  -0.0024   0.0217   1.0000
  10.500   0.8358   0.08731   0.08038  -0.0067   0.0219   1.0000
  10.750   0.8229   0.09420   0.08732  -0.0115   0.0222   1.0000
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