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MH33 (mh33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH33 (mh33-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.17 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh33-il-1000000.txt
Download as CSV file: xf-mh33-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH33                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5502   0.07941   0.07784  -0.0177   1.0000   0.0048
  -8.500  -0.5549   0.07464   0.07310  -0.0206   1.0000   0.0049
  -8.250  -0.5655   0.06936   0.06786  -0.0248   1.0000   0.0048
  -8.000  -0.5737   0.06298   0.06145  -0.0299   1.0000   0.0048
  -7.750  -0.5777   0.05641   0.05479  -0.0331   1.0000   0.0048
  -7.500  -0.5805   0.05059   0.04885  -0.0341   1.0000   0.0048
  -7.250  -0.5823   0.04557   0.04368  -0.0335   1.0000   0.0049
  -7.000  -0.5826   0.04134   0.03928  -0.0318   1.0000   0.0050
  -6.750  -0.5808   0.03761   0.03536  -0.0295   1.0000   0.0051
  -6.500  -0.5755   0.03477   0.03234  -0.0273   1.0000   0.0053
  -6.250  -0.5676   0.03219   0.02959  -0.0250   1.0000   0.0055
  -6.000  -0.5565   0.02930   0.02647  -0.0231   0.9998   0.0057
  -5.750  -0.5288   0.02578   0.02262  -0.0243   0.9981   0.0062
  -5.500  -0.4995   0.02246   0.01893  -0.0252   0.9962   0.0069
  -5.250  -0.4706   0.01728   0.01310  -0.0253   0.9944   0.0061
  -5.000  -0.4398   0.01551   0.01110  -0.0259   0.9926   0.0066
  -4.750  -0.4099   0.01369   0.00900  -0.0262   0.9903   0.0066
  -4.500  -0.3793   0.01189   0.00698  -0.0265   0.9882   0.0062
  -4.250  -0.3460   0.01137   0.00641  -0.0278   0.9863   0.0072
  -4.000  -0.3126   0.01043   0.00538  -0.0289   0.9846   0.0075
  -3.750  -0.2787   0.00927   0.00405  -0.0300   0.9831   0.0070
  -3.500  -0.2430   0.00856   0.00322  -0.0316   0.9819   0.0068
  -3.250  -0.2115   0.00808   0.00263  -0.0322   0.9788   0.0068
  -3.000  -0.1787   0.00775   0.00219  -0.0331   0.9756   0.0073
  -2.750  -0.1454   0.00732   0.00181  -0.0342   0.9726   0.0320
  -2.500  -0.1145   0.00650   0.00153  -0.0352   0.9694   0.1697
  -2.250  -0.0882   0.00606   0.00139  -0.0350   0.9634   0.2525
  -1.750  -0.0375   0.00498   0.00116  -0.0343   0.9501   0.5064
  -1.500  -0.0121   0.00466   0.00106  -0.0337   0.9425   0.5850
  -1.250   0.0120   0.00436   0.00099  -0.0328   0.9328   0.6618
  -1.000   0.0363   0.00408   0.00093  -0.0318   0.9223   0.7379
  -0.750   0.0597   0.00381   0.00089  -0.0306   0.9100   0.8143
  -0.500   0.0825   0.00365   0.00090  -0.0290   0.8953   0.8828
  -0.250   0.1066   0.00363   0.00091  -0.0277   0.8774   0.9203
   0.000   0.1313   0.00368   0.00090  -0.0267   0.8555   0.9414
   0.250   0.1568   0.00376   0.00089  -0.0258   0.8283   0.9561
   0.500   0.1833   0.00388   0.00089  -0.0252   0.7961   0.9673
   0.750   0.2146   0.00404   0.00091  -0.0258   0.7590   0.9751
   1.000   0.2458   0.00423   0.00094  -0.0265   0.7186   0.9823
   1.250   0.2842   0.00444   0.00097  -0.0288   0.6714   0.9852
   1.500   0.3204   0.00468   0.00100  -0.0307   0.6192   0.9888
   1.750   0.3542   0.00493   0.00107  -0.0321   0.5665   0.9926
   2.000   0.3896   0.00517   0.00112  -0.0339   0.5164   0.9954
   2.250   0.4258   0.00543   0.00117  -0.0359   0.4628   0.9983
   2.500   0.4578   0.00569   0.00125  -0.0371   0.4111   1.0000
   2.750   0.4802   0.00595   0.00135  -0.0361   0.3648   1.0000
   3.000   0.5027   0.00621   0.00146  -0.0351   0.3237   1.0000
   3.250   0.5252   0.00647   0.00158  -0.0341   0.2843   1.0000
   3.500   0.5476   0.00675   0.00172  -0.0331   0.2454   1.0000
   3.750   0.5700   0.00704   0.00187  -0.0321   0.2099   1.0000
   4.000   0.5920   0.00738   0.00205  -0.0311   0.1712   1.0000
   4.250   0.6144   0.00771   0.00227  -0.0301   0.1391   1.0000
   4.500   0.6369   0.00803   0.00248  -0.0291   0.1117   1.0000
   4.750   0.6592   0.00840   0.00271  -0.0281   0.0834   1.0000
   5.000   0.6814   0.00882   0.00298  -0.0271   0.0552   1.0000
   5.250   0.7046   0.00914   0.00324  -0.0263   0.0408   1.0000
   5.500   0.7280   0.00946   0.00352  -0.0255   0.0295   1.0000
   5.750   0.7517   0.00981   0.00383  -0.0247   0.0201   1.0000
   6.000   0.7755   0.01019   0.00421  -0.0240   0.0128   1.0000
   6.250   0.7998   0.01052   0.00454  -0.0234   0.0099   1.0000
   6.500   0.8227   0.01112   0.00511  -0.0226   0.0031   1.0000
   6.750   0.8465   0.01163   0.00571  -0.0218   0.0024   1.0000
   7.000   0.8698   0.01223   0.00642  -0.0209   0.0021   1.0000
   7.250   0.8927   0.01290   0.00721  -0.0200   0.0019   1.0000
   7.500   0.9148   0.01371   0.00816  -0.0190   0.0019   1.0000
   7.750   0.9357   0.01473   0.00934  -0.0178   0.0018   1.0000
   8.000   0.9550   0.01600   0.01081  -0.0163   0.0018   1.0000
   8.250   0.9730   0.01757   0.01261  -0.0146   0.0019   1.0000
   8.500   0.9878   0.01978   0.01513  -0.0125   0.0019   1.0000
   8.750   0.9954   0.02362   0.01951  -0.0094   0.0021   1.0000
   9.000   0.9980   0.02804   0.02445  -0.0061   0.0024   1.0000
   9.250   0.9909   0.03331   0.03025  -0.0023   0.0026   1.0000
   9.500   0.9824   0.03772   0.03504   0.0009   0.0027   1.0000
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