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MH33 (mh33-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH33 (mh33-il)
Reynolds number: 100,000
Max Cl/Cd: 46.12 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh33-il-100000.txt
Download as CSV file: xf-mh33-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5351   0.10201   0.09713  -0.0097   1.0000   0.0887
  -8.750  -0.5511   0.09905   0.09429  -0.0159   1.0000   0.0904
  -8.500  -0.5692   0.09556   0.09090  -0.0223   1.0000   0.0908
  -8.250  -0.5315   0.09068   0.08596  -0.0132   1.0000   0.0963
  -8.000  -0.5341   0.08722   0.08256  -0.0151   1.0000   0.1001
  -7.750  -0.5553   0.08327   0.07870  -0.0227   1.0000   0.1033
  -7.500  -0.5583   0.07834   0.07380  -0.0251   1.0000   0.1055
  -7.250  -0.5439   0.07538   0.07089  -0.0216   1.0000   0.1094
  -7.000  -0.5665   0.07199   0.06712  -0.0306   1.0000   0.1175
  -6.750  -0.5450   0.06702   0.06247  -0.0261   1.0000   0.1206
  -6.250  -0.4874   0.04856   0.04425  -0.0256   1.0000   0.1396
  -6.000  -0.4872   0.04416   0.03979  -0.0259   1.0000   0.1480
  -5.750  -0.4851   0.04015   0.03565  -0.0260   1.0000   0.1598
  -5.500  -0.5003   0.03999   0.03367  -0.0286   1.0000   0.0628
  -5.250  -0.4838   0.03489   0.02785  -0.0266   1.0000   0.0496
  -5.000  -0.4668   0.03113   0.02369  -0.0249   1.0000   0.0455
  -4.750  -0.4458   0.02768   0.01938  -0.0226   1.0000   0.0408
  -4.500  -0.4230   0.02593   0.01721  -0.0209   1.0000   0.0397
  -4.250  -0.4004   0.02371   0.01467  -0.0194   1.0000   0.0395
  -4.000  -0.3776   0.02113   0.01189  -0.0180   1.0000   0.0404
  -3.750  -0.3558   0.01953   0.01030  -0.0168   1.0000   0.0479
  -3.500  -0.3340   0.01797   0.00873  -0.0153   1.0000   0.0566
  -3.250  -0.3131   0.01632   0.00723  -0.0135   1.0000   0.0874
  -3.000  -0.2993   0.01308   0.00591  -0.0113   1.0000   0.3938
  -2.750  -0.2864   0.01176   0.00581  -0.0075   1.0000   0.6655
  -2.500  -0.2169   0.01172   0.00599  -0.0117   1.0000   0.9578
  -2.250  -0.1281   0.01167   0.00533  -0.0239   1.0000   1.0000
  -2.000  -0.1180   0.01154   0.00501  -0.0211   1.0000   1.0000
  -1.750  -0.1060   0.01146   0.00476  -0.0186   1.0000   1.0000
  -1.500  -0.0926   0.01142   0.00456  -0.0162   1.0000   1.0000
  -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  -0.0293   0.01159   0.00418  -0.0085   1.0000   1.0000
  -0.250  -0.0115   0.01171   0.00421  -0.0071   1.0000   1.0000
   0.000   0.0065   0.01185   0.00429  -0.0057   1.0000   1.0000
   0.250   0.0247   0.01203   0.00437  -0.0044   1.0000   1.0000
   0.500   0.0430   0.01225   0.00455  -0.0033   1.0000   1.0000
   0.750   0.0611   0.01251   0.00477  -0.0022   1.0000   1.0000
   1.000   0.0789   0.01281   0.00506  -0.0012   1.0000   1.0000
   1.250   0.1089   0.01323   0.00550  -0.0028   0.9958   1.0000
   1.500   0.1714   0.01377   0.00611  -0.0104   0.9810   1.0000
   1.750   0.2297   0.01403   0.00645  -0.0168   0.9631   1.0000
   2.000   0.2898   0.01409   0.00666  -0.0232   0.9450   1.0000
   2.250   0.3530   0.01388   0.00668  -0.0297   0.9267   1.0000
   2.500   0.4084   0.01347   0.00647  -0.0342   0.9041   1.0000
   2.750   0.4548   0.01299   0.00616  -0.0365   0.8766   1.0000
   3.000   0.4905   0.01259   0.00596  -0.0365   0.8402   1.0000
   3.250   0.5225   0.01229   0.00571  -0.0356   0.7949   1.0000
   3.500   0.5487   0.01223   0.00561  -0.0338   0.7378   1.0000
   3.750   0.5714   0.01243   0.00564  -0.0315   0.6718   1.0000
   4.000   0.5917   0.01283   0.00580  -0.0291   0.5991   1.0000
   4.250   0.6108   0.01340   0.00613  -0.0267   0.5235   1.0000
   4.500   0.6291   0.01410   0.00651  -0.0245   0.4462   1.0000
   4.750   0.6471   0.01493   0.00700  -0.0225   0.3699   1.0000
   5.000   0.6652   0.01588   0.00761  -0.0207   0.2988   1.0000
   5.250   0.6835   0.01700   0.00840  -0.0191   0.2358   1.0000
   5.500   0.7021   0.01821   0.00933  -0.0176   0.1819   1.0000
   5.750   0.7213   0.01961   0.01052  -0.0160   0.1401   1.0000
   6.000   0.7405   0.02124   0.01188  -0.0147   0.1084   1.0000
   6.250   0.7615   0.02272   0.01340  -0.0133   0.0852   1.0000
   6.500   0.7835   0.02471   0.01547  -0.0122   0.0709   1.0000
   6.750   0.8079   0.02721   0.01831  -0.0109   0.0637   1.0000
   7.000   0.8305   0.03025   0.02145  -0.0099   0.0579   1.0000
   7.250   0.8490   0.03241   0.02422  -0.0080   0.0507   1.0000
   7.500   0.8670   0.03565   0.02778  -0.0064   0.0473   1.0000
   7.750   0.8767   0.04133   0.03383  -0.0047   0.0450   1.0000
   8.000   0.8842   0.04380   0.03715  -0.0018   0.0416   1.0000
   8.250   0.8877   0.04809   0.04199   0.0004   0.0403   1.0000
   8.500   0.8863   0.05307   0.04741   0.0023   0.0412   1.0000
   8.750   0.8801   0.05822   0.05292   0.0039   0.0419   1.0000
   9.000   0.8725   0.06304   0.05797   0.0050   0.0429   1.0000
   9.250   0.8630   0.06795   0.06302   0.0058   0.0439   1.0000
   9.500   0.8019   0.08174   0.07733   0.0000   0.0738   1.0000
   9.750   0.7947   0.08668   0.08227  -0.0022   0.0722   1.0000
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