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MH33 (mh33-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH33 (mh33-il)
Reynolds number: 50,000
Max Cl/Cd: 31.86 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh33-il-50000-n5.txt
Download as CSV file: xf-mh33-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5379   0.09348   0.08655  -0.0144   1.0000   0.0327
  -8.500  -0.5400   0.08890   0.08205  -0.0170   1.0000   0.0317
  -8.250  -0.5440   0.08407   0.07731  -0.0201   1.0000   0.0309
  -8.000  -0.5517   0.07833   0.07165  -0.0245   1.0000   0.0297
  -7.750  -0.5595   0.07131   0.06454  -0.0296   1.0000   0.0280
  -7.250  -0.5582   0.06287   0.05578  -0.0317   1.0000   0.0272
  -7.000  -0.5558   0.05865   0.05137  -0.0320   1.0000   0.0271
  -6.750  -0.5512   0.05453   0.04696  -0.0320   1.0000   0.0273
  -6.250  -0.5361   0.04658   0.03844  -0.0309   1.0000   0.0282
  -6.000  -0.5248   0.04347   0.03511  -0.0301   1.0000   0.0296
  -5.750  -0.5107   0.04061   0.03196  -0.0291   1.0000   0.0313
  -5.500  -0.4946   0.03756   0.02848  -0.0279   1.0000   0.0326
  -5.250  -0.4763   0.03459   0.02502  -0.0265   1.0000   0.0336
  -5.000  -0.4559   0.03182   0.02164  -0.0251   1.0000   0.0345
  -4.750  -0.4338   0.02932   0.01869  -0.0236   1.0000   0.0360
  -4.500  -0.4108   0.02721   0.01617  -0.0220   1.0000   0.0383
  -4.250  -0.3898   0.02546   0.01435  -0.0207   1.0000   0.0459
  -4.000  -0.3676   0.02384   0.01256  -0.0193   1.0000   0.0558
  -3.750  -0.3449   0.02222   0.01081  -0.0179   1.0000   0.0772
  -3.500  -0.3224   0.02030   0.00929  -0.0171   1.0000   0.1385
  -3.250  -0.3040   0.01845   0.00835  -0.0160   1.0000   0.2945
  -3.000  -0.2891   0.01708   0.00787  -0.0135   1.0000   0.4813
  -2.750  -0.2747   0.01611   0.00765  -0.0094   1.0000   0.6669
  -2.500  -0.2153   0.01584   0.00738  -0.0123   1.0000   0.9090
  -2.250  -0.1304   0.01574   0.00656  -0.0233   1.0000   1.0000
  -2.000  -0.1167   0.01560   0.00616  -0.0212   1.0000   1.0000
  -1.750  -0.1021   0.01551   0.00583  -0.0192   1.0000   1.0000
  -1.500  -0.0869   0.01546   0.00556  -0.0172   1.0000   1.0000
  -1.250  -0.0709   0.01544   0.00528  -0.0154   1.0000   1.0000
  -1.000  -0.0543   0.01545   0.00512  -0.0136   1.0000   1.0000
  -0.750  -0.0371   0.01549   0.00500  -0.0120   1.0000   1.0000
  -0.500  -0.0194   0.01555   0.00493  -0.0105   1.0000   1.0000
  -0.250  -0.0013   0.01564   0.00490  -0.0090   1.0000   1.0000
   0.000   0.0170   0.01576   0.00493  -0.0077   1.0000   1.0000
   0.250   0.0354   0.01591   0.00496  -0.0064   1.0000   1.0000
   0.500   0.0539   0.01609   0.00508  -0.0053   1.0000   1.0000
   0.750   0.0723   0.01630   0.00526  -0.0042   1.0000   1.0000
   1.000   0.0906   0.01655   0.00549  -0.0031   1.0000   1.0000
   1.250   0.1367   0.01697   0.00595  -0.0076   0.9854   1.0000
   1.500   0.1868   0.01735   0.00640  -0.0126   0.9687   1.0000
   1.750   0.2330   0.01758   0.00673  -0.0165   0.9489   1.0000
   2.000   0.2820   0.01773   0.00703  -0.0208   0.9289   1.0000
   2.250   0.3265   0.01777   0.00729  -0.0239   0.9052   1.0000
   2.500   0.3691   0.01771   0.00743  -0.0263   0.8790   1.0000
   2.750   0.4089   0.01759   0.00750  -0.0278   0.8491   1.0000
   3.000   0.4443   0.01747   0.00756  -0.0282   0.8127   1.0000
   3.250   0.4795   0.01736   0.00768  -0.0283   0.7702   1.0000
   3.500   0.5110   0.01735   0.00774  -0.0277   0.7202   1.0000
   3.750   0.5386   0.01749   0.00785  -0.0263   0.6625   1.0000
   4.000   0.5622   0.01781   0.00806  -0.0244   0.5996   1.0000
   4.250   0.5833   0.01831   0.00839  -0.0222   0.5343   1.0000
   4.500   0.6029   0.01894   0.00892  -0.0201   0.4686   1.0000
   4.750   0.6223   0.01971   0.00949  -0.0183   0.4038   1.0000
   5.000   0.6417   0.02057   0.01018  -0.0168   0.3411   1.0000
   5.250   0.6610   0.02157   0.01098  -0.0154   0.2826   1.0000
   5.500   0.6807   0.02268   0.01193  -0.0142   0.2294   1.0000
   5.750   0.7008   0.02390   0.01303  -0.0131   0.1823   1.0000
   6.000   0.7210   0.02531   0.01433  -0.0121   0.1455   1.0000
   6.250   0.7412   0.02680   0.01583  -0.0109   0.1149   1.0000
   6.500   0.7612   0.02850   0.01765  -0.0097   0.0931   1.0000
   6.750   0.7816   0.03022   0.01954  -0.0086   0.0757   1.0000
   7.000   0.8030   0.03249   0.02199  -0.0073   0.0660   1.0000
   7.250   0.8216   0.03442   0.02403  -0.0062   0.0557   1.0000
   7.500   0.8415   0.03686   0.02691  -0.0049   0.0488   1.0000
   7.750   0.8589   0.03988   0.03007  -0.0038   0.0451   1.0000
   8.000   0.8738   0.04374   0.03462  -0.0021   0.0431   1.0000
   8.250   0.8828   0.04791   0.03943  -0.0003   0.0412   1.0000
   8.500   0.8878   0.05152   0.04352   0.0013   0.0380   1.0000
   8.750   0.8950   0.05374   0.04574   0.0023   0.0338   1.0000
   9.000   0.8916   0.05801   0.05038   0.0037   0.0327   1.0000
   9.250   0.8832   0.06243   0.05520   0.0049   0.0324   1.0000
   9.500   0.8716   0.06668   0.05972   0.0057   0.0324   1.0000
   9.750   0.8547   0.07087   0.06408   0.0063   0.0324   1.0000
  10.000   0.8388   0.07537   0.06869   0.0053   0.0326   1.0000
  10.250   0.8218   0.08090   0.07431   0.0024   0.0328   1.0000
  10.500   0.8079   0.08706   0.08050  -0.0018   0.0330   1.0000
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