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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 100,000
Max Cl/Cd: 47.81 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh22-il-100000-n5.txt
Download as CSV file: xf-mh22-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5174   0.08881   0.08417  -0.0003   1.0000   0.0135
  -7.750  -0.5170   0.08483   0.08026  -0.0027   1.0000   0.0137
  -7.500  -0.5177   0.08094   0.07643  -0.0050   1.0000   0.0128
  -7.250  -0.5169   0.07647   0.07201  -0.0087   1.0000   0.0128
  -7.000  -0.5127   0.07153   0.06708  -0.0128   1.0000   0.0129
  -6.750  -0.5061   0.06630   0.06182  -0.0170   1.0000   0.0132
  -6.500  -0.4971   0.06086   0.05631  -0.0206   1.0000   0.0135
  -6.250  -0.4860   0.05525   0.05055  -0.0237   1.0000   0.0140
  -6.000  -0.4729   0.05005   0.04514  -0.0256   1.0000   0.0141
  -5.750  -0.4580   0.04488   0.03967  -0.0269   1.0000   0.0146
  -5.500  -0.4416   0.04014   0.03455  -0.0273   1.0000   0.0150
  -5.250  -0.4239   0.03583   0.02978  -0.0272   1.0000   0.0152
  -5.000  -0.4049   0.03198   0.02543  -0.0266   1.0000   0.0151
  -4.750  -0.3842   0.02853   0.02144  -0.0257   1.0000   0.0152
  -4.500  -0.3620   0.02563   0.01802  -0.0247   1.0000   0.0154
  -4.250  -0.3388   0.02316   0.01495  -0.0235   1.0000   0.0158
  -4.000  -0.3154   0.02120   0.01267  -0.0224   1.0000   0.0163
  -3.750  -0.2934   0.01922   0.01050  -0.0211   1.0000   0.0171
  -3.500  -0.2728   0.01771   0.00886  -0.0197   1.0000   0.0188
  -3.250  -0.2524   0.01667   0.00771  -0.0184   0.9995   0.0219
  -3.000  -0.2152   0.01537   0.00642  -0.0204   0.9810   0.0445
  -2.750  -0.1807   0.01402   0.00563  -0.0222   0.9619   0.1525
  -2.500  -0.1451   0.01323   0.00514  -0.0241   0.9439   0.2522
  -2.250  -0.1115   0.01240   0.00475  -0.0256   0.9262   0.3919
  -2.000  -0.0831   0.01138   0.00453  -0.0254   0.9085   0.6216
  -1.750  -0.0114   0.01060   0.00421  -0.0323   0.9044   0.9427
  -1.500   0.0452   0.01055   0.00383  -0.0381   0.8901   1.0000
  -1.250   0.0726   0.01060   0.00362  -0.0379   0.8680   1.0000
  -1.000   0.0978   0.01067   0.00345  -0.0372   0.8489   1.0000
  -0.750   0.1221   0.01075   0.00326  -0.0363   0.8310   1.0000
  -0.500   0.1462   0.01085   0.00317  -0.0354   0.8149   1.0000
  -0.250   0.1703   0.01095   0.00311  -0.0345   0.8000   1.0000
   0.000   0.1946   0.01105   0.00308  -0.0336   0.7860   1.0000
   0.250   0.2189   0.01116   0.00307  -0.0327   0.7726   1.0000
   0.500   0.2433   0.01128   0.00309  -0.0319   0.7595   1.0000
   0.750   0.2680   0.01140   0.00314  -0.0311   0.7466   1.0000
   1.000   0.2928   0.01153   0.00319  -0.0304   0.7337   1.0000
   1.250   0.3176   0.01166   0.00326  -0.0297   0.7208   1.0000
   1.500   0.3424   0.01180   0.00334  -0.0289   0.7077   1.0000
   1.750   0.3673   0.01194   0.00345  -0.0282   0.6945   1.0000
   2.000   0.3922   0.01208   0.00357  -0.0275   0.6810   1.0000
   2.250   0.4171   0.01223   0.00377  -0.0267   0.6671   1.0000
   2.500   0.4421   0.01237   0.00392  -0.0260   0.6526   1.0000
   2.750   0.4671   0.01252   0.00407  -0.0252   0.6377   1.0000
   3.000   0.4922   0.01267   0.00426  -0.0246   0.6209   1.0000
   3.250   0.5173   0.01282   0.00447  -0.0239   0.6029   1.0000
   3.500   0.5423   0.01298   0.00477  -0.0231   0.5841   1.0000
   3.750   0.5674   0.01313   0.00501  -0.0224   0.5620   1.0000
   4.000   0.5923   0.01330   0.00525  -0.0217   0.5379   1.0000
   4.250   0.6170   0.01349   0.00549  -0.0209   0.5111   1.0000
   4.500   0.6414   0.01373   0.00576  -0.0200   0.4817   1.0000
   4.750   0.6655   0.01403   0.00608  -0.0191   0.4498   1.0000
   5.000   0.6892   0.01442   0.00648  -0.0182   0.4148   1.0000
   5.250   0.7124   0.01490   0.00694  -0.0173   0.3732   1.0000
   5.500   0.7346   0.01551   0.00747  -0.0164   0.3157   1.0000
   5.750   0.7522   0.01685   0.00834  -0.0153   0.1883   1.0000
   6.250   0.7798   0.02197   0.01222  -0.0123   0.0152   1.0000
   6.500   0.7991   0.02340   0.01386  -0.0111   0.0109   1.0000
   6.750   0.8186   0.02467   0.01532  -0.0101   0.0083   1.0000
   7.000   0.8360   0.02635   0.01719  -0.0088   0.0073   1.0000
   7.250   0.8525   0.02836   0.01941  -0.0073   0.0069   1.0000
   7.500   0.8685   0.03079   0.02208  -0.0059   0.0065   1.0000
   7.750   0.8845   0.03354   0.02511  -0.0045   0.0063   1.0000
   8.000   0.8987   0.03672   0.02865  -0.0031   0.0062   1.0000
   8.250   0.9104   0.04003   0.03235  -0.0017   0.0061   1.0000
   8.500   0.9188   0.04341   0.03613  -0.0004   0.0061   1.0000
   8.750   0.9230   0.04691   0.04002   0.0010   0.0061   1.0000
   9.000   0.9230   0.05041   0.04388   0.0023   0.0061   1.0000
   9.250   0.9197   0.05371   0.04748   0.0035   0.0061   1.0000
   9.500   0.9092   0.05699   0.05100   0.0048   0.0061   1.0000
   9.750   0.8972   0.06049   0.05471   0.0049   0.0062   1.0000
  10.000   0.8865   0.06432   0.05872   0.0037   0.0062   1.0000
  10.250   0.8746   0.06892   0.06349   0.0012   0.0063   1.0000
  10.500   0.8604   0.07460   0.06933  -0.0025   0.0063   1.0000
  10.750   0.8471   0.08103   0.07589  -0.0072   0.0064   1.0000
  11.000   0.8357   0.08817   0.08315  -0.0124   0.0065   1.0000
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