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MH33 (mh33-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH33 (mh33-il)
Reynolds number: 100,000
Max Cl/Cd: 42.16 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh33-il-100000-n5.txt
Download as CSV file: xf-mh33-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4503   0.10452   0.09971  -0.0094   1.0000   0.0234
  -9.750  -0.5377   0.10698   0.10186  -0.0069   1.0000   0.0247
  -9.500  -0.5361   0.10277   0.09769  -0.0083   1.0000   0.0232
  -9.250  -0.5351   0.09867   0.09363  -0.0100   1.0000   0.0222
  -9.000  -0.5361   0.09403   0.08904  -0.0122   1.0000   0.0211
  -8.750  -0.5379   0.08938   0.08446  -0.0146   1.0000   0.0202
  -8.500  -0.5423   0.08408   0.07923  -0.0178   1.0000   0.0193
  -8.000  -0.5533   0.07087   0.06611  -0.0286   1.0000   0.0173
  -7.750  -0.5514   0.06664   0.06177  -0.0303   1.0000   0.0168
  -7.500  -0.5549   0.06204   0.05711  -0.0315   1.0000   0.0165
  -7.250  -0.5561   0.05752   0.05247  -0.0323   1.0000   0.0163
  -7.000  -0.5552   0.05304   0.04782  -0.0325   1.0000   0.0161
  -6.750  -0.5518   0.04872   0.04326  -0.0322   1.0000   0.0159
  -6.500  -0.5461   0.04461   0.03885  -0.0314   1.0000   0.0156
  -6.250  -0.5377   0.04075   0.03465  -0.0302   1.0000   0.0155
  -6.000  -0.5269   0.03714   0.03063  -0.0288   1.0000   0.0153
  -5.750  -0.5135   0.03377   0.02681  -0.0272   1.0000   0.0152
  -5.500  -0.4978   0.03074   0.02331  -0.0255   1.0000   0.0151
  -5.250  -0.4799   0.02805   0.02016  -0.0239   1.0000   0.0151
  -5.000  -0.4602   0.02569   0.01739  -0.0223   1.0000   0.0152
  -4.750  -0.4394   0.02363   0.01487  -0.0208   1.0000   0.0155
  -4.500  -0.4180   0.02189   0.01287  -0.0193   1.0000   0.0159
  -4.250  -0.3967   0.02038   0.01115  -0.0178   1.0000   0.0165
  -4.000  -0.3762   0.01892   0.00955  -0.0163   1.0000   0.0178
  -3.750  -0.3554   0.01791   0.00848  -0.0152   1.0000   0.0236
  -3.500  -0.3341   0.01685   0.00727  -0.0138   1.0000   0.0295
  -3.250  -0.3128   0.01559   0.00616  -0.0125   1.0000   0.0619
  -3.000  -0.2930   0.01418   0.00552  -0.0115   1.0000   0.1960
  -2.750  -0.2726   0.01326   0.00518  -0.0105   1.0000   0.3340
  -2.500  -0.2523   0.01253   0.00494  -0.0092   1.0000   0.4693
  -2.250  -0.2328   0.01192   0.00474  -0.0072   1.0000   0.6064
  -2.000  -0.2137   0.01146   0.00475  -0.0045   1.0000   0.7534
  -1.750  -0.1641   0.01140   0.00483  -0.0074   1.0000   0.9263
  -1.500  -0.0977   0.01141   0.00456  -0.0152   1.0000   0.9958
  -1.250  -0.0783   0.01142   0.00437  -0.0140   1.0000   1.0000
  -1.000  -0.0628   0.01145   0.00426  -0.0120   1.0000   1.0000
  -0.750  -0.0465   0.01151   0.00420  -0.0102   1.0000   1.0000
  -0.500  -0.0102   0.01164   0.00421  -0.0124   0.9940   1.0000
  -0.250   0.0326   0.01176   0.00422  -0.0158   0.9847   1.0000
   0.000   0.0748   0.01185   0.00421  -0.0190   0.9748   1.0000
   0.250   0.1176   0.01191   0.00423  -0.0222   0.9645   1.0000
   0.500   0.1618   0.01193   0.00424  -0.0257   0.9540   1.0000
   0.750   0.2044   0.01190   0.00422  -0.0287   0.9417   1.0000
   1.000   0.2407   0.01183   0.00417  -0.0303   0.9254   1.0000
   1.250   0.2753   0.01176   0.00413  -0.0314   0.9068   1.0000
   1.500   0.3104   0.01167   0.00408  -0.0325   0.8862   1.0000
   1.750   0.3438   0.01159   0.00407  -0.0332   0.8612   1.0000
   2.000   0.3749   0.01152   0.00402  -0.0333   0.8304   1.0000
   2.250   0.4065   0.01147   0.00396  -0.0334   0.7942   1.0000
   2.500   0.4352   0.01151   0.00394  -0.0329   0.7502   1.0000
   2.750   0.4617   0.01164   0.00396  -0.0319   0.7002   1.0000
   3.000   0.4859   0.01188   0.00411  -0.0307   0.6452   1.0000
   3.250   0.5087   0.01222   0.00427  -0.0292   0.5873   1.0000
   3.500   0.5305   0.01262   0.00448  -0.0278   0.5289   1.0000
   3.750   0.5519   0.01309   0.00475  -0.0263   0.4708   1.0000
   4.000   0.5732   0.01360   0.00507  -0.0250   0.4138   1.0000
   4.250   0.5945   0.01415   0.00552  -0.0238   0.3589   1.0000
   4.500   0.6158   0.01475   0.00595  -0.0226   0.3055   1.0000
   4.750   0.6370   0.01540   0.00643  -0.0215   0.2550   1.0000
   5.000   0.6585   0.01607   0.00698  -0.0205   0.2083   1.0000
   5.250   0.6800   0.01681   0.00761  -0.0195   0.1679   1.0000
   5.500   0.7012   0.01762   0.00831  -0.0186   0.1307   1.0000
   5.750   0.7223   0.01851   0.00914  -0.0175   0.1014   1.0000
   6.000   0.7430   0.01948   0.01004  -0.0165   0.0749   1.0000
   6.250   0.7629   0.02063   0.01128  -0.0153   0.0585   1.0000
   6.500   0.7826   0.02180   0.01245  -0.0141   0.0445   1.0000
   6.750   0.8025   0.02308   0.01394  -0.0127   0.0376   1.0000
   7.000   0.8196   0.02495   0.01586  -0.0111   0.0331   1.0000
   7.250   0.8402   0.02671   0.01794  -0.0097   0.0296   1.0000
   7.500   0.8594   0.02796   0.01934  -0.0087   0.0240   1.0000
   7.750   0.8758   0.03096   0.02261  -0.0070   0.0215   1.0000
   8.000   0.8933   0.03346   0.02561  -0.0054   0.0185   1.0000
   8.250   0.9086   0.03504   0.02745  -0.0042   0.0152   1.0000
   8.500   0.9188   0.03791   0.03061  -0.0026   0.0139   1.0000
   8.750   0.9195   0.04267   0.03585  -0.0003   0.0131   1.0000
   9.000   0.9213   0.04637   0.04005   0.0018   0.0128   1.0000
   9.250   0.9167   0.05038   0.04451   0.0039   0.0125   1.0000
   9.500   0.9085   0.05416   0.04861   0.0056   0.0125   1.0000
   9.750   0.8913   0.05802   0.05275   0.0076   0.0124   1.0000
  10.000   0.8760   0.06183   0.05673   0.0080   0.0126   1.0000
  10.250   0.8562   0.06699   0.06207   0.0059   0.0126   1.0000
  10.500   0.8396   0.07301   0.06821   0.0016   0.0127   1.0000
  10.750   0.8232   0.08079   0.07608  -0.0047   0.0129   1.0000
  11.000   0.8095   0.08917   0.08448  -0.0108   0.0131   1.0000
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