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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 50,000
Max Cl/Cd: 37.91 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh32-il-50000-n5.txt
Download as CSV file: xf-mh32-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4290   0.09207   0.08524  -0.0324   1.0000   0.0359
  -8.250  -0.4277   0.08843   0.08168  -0.0331   1.0000   0.0354
  -8.000  -0.4282   0.08492   0.07825  -0.0341   1.0000   0.0349
  -7.750  -0.4316   0.08124   0.07467  -0.0355   1.0000   0.0344
  -7.500  -0.4333   0.07728   0.07079  -0.0376   1.0000   0.0339
  -7.250  -0.4355   0.07292   0.06648  -0.0399   1.0000   0.0334
  -7.000  -0.4368   0.06886   0.06244  -0.0414   1.0000   0.0328
  -6.750  -0.4386   0.06462   0.05817  -0.0425   1.0000   0.0325
  -6.500  -0.4386   0.06060   0.05408  -0.0432   1.0000   0.0320
  -6.250  -0.4372   0.05654   0.04988  -0.0436   1.0000   0.0315
  -6.000  -0.4335   0.05245   0.04557  -0.0437   1.0000   0.0313
  -5.750  -0.4268   0.04853   0.04136  -0.0435   1.0000   0.0311
  -5.500  -0.4171   0.04480   0.03728  -0.0430   1.0000   0.0315
  -5.250  -0.4044   0.04130   0.03332  -0.0424   1.0000   0.0328
  -5.000  -0.3886   0.03809   0.02954  -0.0416   1.0000   0.0346
  -4.750  -0.3702   0.03530   0.02613  -0.0406   1.0000   0.0360
  -4.500  -0.3515   0.03251   0.02297  -0.0397   1.0000   0.0376
  -4.250  -0.3315   0.03023   0.02039  -0.0387   1.0000   0.0394
  -4.000  -0.3101   0.02827   0.01813  -0.0375   1.0000   0.0421
  -3.750  -0.2877   0.02674   0.01609  -0.0362   1.0000   0.0484
  -3.500  -0.2669   0.02527   0.01459  -0.0351   1.0000   0.0563
  -3.250  -0.2446   0.02382   0.01297  -0.0338   1.0000   0.0666
  -3.000  -0.2219   0.02268   0.01173  -0.0329   1.0000   0.0894
  -2.750  -0.1984   0.02138   0.01065  -0.0325   1.0000   0.1379
  -2.500  -0.1753   0.01985   0.00992  -0.0325   1.0000   0.2821
  -2.250  -0.1572   0.01873   0.00973  -0.0310   1.0000   0.4866
  -2.000  -0.1454   0.01796   0.00975  -0.0269   1.0000   0.6867
  -1.750  -0.0987   0.01739   0.00929  -0.0292   0.9971   1.0000
  -1.500  -0.0580   0.01767   0.00903  -0.0325   0.9878   1.0000
  -1.250  -0.0175   0.01798   0.00890  -0.0356   0.9786   1.0000
  -1.000   0.0237   0.01829   0.00883  -0.0389   0.9692   1.0000
  -0.750   0.0616   0.01855   0.00876  -0.0414   0.9585   1.0000
  -0.500   0.0997   0.01880   0.00875  -0.0438   0.9476   1.0000
  -0.250   0.1383   0.01905   0.00879  -0.0463   0.9368   1.0000
   0.000   0.1782   0.01928   0.00881  -0.0490   0.9262   1.0000
   0.250   0.2174   0.01947   0.00886  -0.0514   0.9151   1.0000
   0.500   0.2536   0.01965   0.00893  -0.0532   0.9028   1.0000
   0.750   0.2896   0.01980   0.00902  -0.0548   0.8904   1.0000
   1.000   0.3241   0.01993   0.00908  -0.0561   0.8775   1.0000
   1.250   0.3578   0.02004   0.00916  -0.0571   0.8642   1.0000
   1.500   0.3906   0.02012   0.00922  -0.0579   0.8504   1.0000
   1.750   0.4228   0.02017   0.00930  -0.0584   0.8361   1.0000
   2.000   0.4546   0.02019   0.00934  -0.0587   0.8213   1.0000
   2.250   0.4862   0.02018   0.00935  -0.0589   0.8061   1.0000
   2.500   0.5132   0.02023   0.00944  -0.0583   0.7881   1.0000
   2.750   0.5416   0.02024   0.00949  -0.0578   0.7702   1.0000
   3.000   0.5713   0.02019   0.00956  -0.0574   0.7528   1.0000
   3.250   0.5978   0.02023   0.00967  -0.0566   0.7327   1.0000
   3.500   0.6259   0.02022   0.00972  -0.0559   0.7128   1.0000
   3.750   0.6522   0.02028   0.00985  -0.0549   0.6907   1.0000
   4.000   0.6797   0.02030   0.00998  -0.0540   0.6685   1.0000
   4.250   0.7056   0.02041   0.01015  -0.0530   0.6439   1.0000
   4.500   0.7308   0.02058   0.01037  -0.0518   0.6177   1.0000
   4.750   0.7556   0.02079   0.01063  -0.0506   0.5903   1.0000
   5.000   0.7798   0.02107   0.01101  -0.0494   0.5615   1.0000
   5.250   0.8028   0.02144   0.01142  -0.0480   0.5310   1.0000
   5.500   0.8250   0.02186   0.01189  -0.0467   0.4991   1.0000
   5.750   0.8468   0.02234   0.01239  -0.0452   0.4669   1.0000
   6.000   0.8676   0.02290   0.01298  -0.0438   0.4334   1.0000
   6.250   0.8877   0.02354   0.01362  -0.0423   0.3996   1.0000
   6.500   0.9069   0.02426   0.01436  -0.0408   0.3651   1.0000
   6.750   0.9251   0.02507   0.01526  -0.0392   0.3307   1.0000
   7.000   0.9425   0.02598   0.01618  -0.0377   0.2962   1.0000
   7.250   0.9588   0.02700   0.01718  -0.0360   0.2626   1.0000
   7.500   0.9743   0.02815   0.01833  -0.0344   0.2297   1.0000
   7.750   0.9885   0.02942   0.01959  -0.0328   0.1973   1.0000
   8.000   1.0010   0.03084   0.02096  -0.0311   0.1675   1.0000
   8.250   1.0126   0.03244   0.02252  -0.0293   0.1403   1.0000
   8.500   1.0233   0.03420   0.02428  -0.0275   0.1156   1.0000
   8.750   1.0335   0.03613   0.02625  -0.0257   0.0956   1.0000
   9.000   1.0425   0.03816   0.02833  -0.0239   0.0797   1.0000
   9.250   1.0544   0.04060   0.03102  -0.0220   0.0691   1.0000
   9.500   1.0623   0.04289   0.03341  -0.0202   0.0596   1.0000
   9.750   1.0665   0.04507   0.03566  -0.0182   0.0520   1.0000
  10.000   1.0790   0.04828   0.03925  -0.0166   0.0466   1.0000
  10.250   1.0815   0.05082   0.04197  -0.0148   0.0419   1.0000
  10.500   1.0818   0.05377   0.04502  -0.0132   0.0384   1.0000
  10.750   1.0795   0.05733   0.04905  -0.0116   0.0356   1.0000
  11.000   1.0750   0.06121   0.05328  -0.0105   0.0344   1.0000
  11.250   1.0664   0.06536   0.05773  -0.0099   0.0334   1.0000
  11.500   1.0546   0.06986   0.06251  -0.0101   0.0329   1.0000
  11.750   1.0400   0.07487   0.06777  -0.0112   0.0325   1.0000
  12.000   1.0227   0.08072   0.07387  -0.0135   0.0326   1.0000
  12.250   1.0032   0.08749   0.08084  -0.0171   0.0331   1.0000
  12.500   0.9811   0.09552   0.08906  -0.0220   0.0339   1.0000
  12.750   0.9592   0.10454   0.09822  -0.0279   0.0348   1.0000
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