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MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 84 13.69% (mh84-il)
Reynolds number: 200,000
Max Cl/Cd: 62.47 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh84-il-200000.txt
Download as CSV file: xf-mh84-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 84  13.69%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2628   0.11450   0.11139  -0.0057   1.0000   0.0492
  -9.500  -0.2555   0.11127   0.10821  -0.0079   1.0000   0.0505
  -9.250  -0.2675   0.10657   0.10360  -0.0148   1.0000   0.0523
  -9.000  -0.2477   0.10369   0.10078  -0.0144   1.0000   0.0528
  -8.750  -0.2194   0.10037   0.09741  -0.0176   0.9310   0.0546
  -8.500  -0.2379   0.09535   0.09232  -0.0280   0.8881   0.0585
  -8.250  -0.2211   0.09282   0.08970  -0.0251   0.8628   0.0589
  -8.000  -0.2043   0.09106   0.08785  -0.0225   0.8409   0.0601
  -7.750  -0.1964   0.08875   0.08546  -0.0224   0.8216   0.0615
  -7.500  -0.1938   0.08589   0.08255  -0.0238   0.8045   0.0637
  -7.250  -0.2176   0.08069   0.07738  -0.0309   0.7899   0.0659
  -7.000  -0.1993   0.07870   0.07531  -0.0285   0.7758   0.0666
  -6.750  -0.1876   0.07664   0.07318  -0.0277   0.7621   0.0678
  -6.500  -0.1821   0.07424   0.07077  -0.0283   0.7482   0.0692
  -6.250  -0.2402   0.03289   0.02768  -0.0726   0.7534   0.0366
  -6.000  -0.2176   0.02997   0.02439  -0.0731   0.7422   0.0357
  -5.750  -0.1929   0.02712   0.02114  -0.0739   0.7298   0.0352
  -5.500  -0.1674   0.02472   0.01824  -0.0741   0.7193   0.0349
  -5.250  -0.1399   0.02279   0.01593  -0.0742   0.7067   0.0349
  -5.000  -0.1123   0.02131   0.01407  -0.0740   0.6957   0.0354
  -4.750  -0.0841   0.02011   0.01252  -0.0737   0.6839   0.0362
  -4.500  -0.0566   0.01899   0.01135  -0.0734   0.6724   0.0374
  -4.250  -0.0289   0.01820   0.01045  -0.0730   0.6615   0.0391
  -4.000  -0.0004   0.01742   0.00958  -0.0728   0.6495   0.0419
  -3.750   0.0276   0.01692   0.00893  -0.0724   0.6393   0.0460
  -3.500   0.0563   0.01622   0.00828  -0.0723   0.6270   0.0510
  -3.250   0.0848   0.01559   0.00759  -0.0720   0.6168   0.0589
  -3.000   0.1137   0.01497   0.00705  -0.0720   0.6052   0.0758
  -2.750   0.1426   0.01445   0.00663  -0.0719   0.5946   0.1104
  -2.500   0.1714   0.01425   0.00640  -0.0718   0.5836   0.1446
  -2.250   0.2003   0.01414   0.00635  -0.0717   0.5725   0.1721
  -2.000   0.2290   0.01412   0.00623  -0.0714   0.5624   0.1971
  -1.750   0.2579   0.01403   0.00619  -0.0713   0.5510   0.2203
  -1.500   0.2863   0.01401   0.00608  -0.0711   0.5415   0.2434
  -1.250   0.3153   0.01390   0.00600  -0.0710   0.5300   0.2664
  -1.000   0.3438   0.01385   0.00588  -0.0707   0.5206   0.2893
  -0.750   0.3727   0.01375   0.00579  -0.0706   0.5097   0.3130
  -0.500   0.4011   0.01367   0.00572  -0.0704   0.5003   0.3380
  -0.250   0.4297   0.01355   0.00567  -0.0702   0.4899   0.3665
   0.000   0.4580   0.01349   0.00564  -0.0700   0.4806   0.4012
   0.250   0.4862   0.01335   0.00564  -0.0698   0.4706   0.4468
   0.500   0.5139   0.01323   0.00569  -0.0695   0.4615   0.5135
   0.750   0.5402   0.01299   0.00576  -0.0688   0.4521   0.6152
   1.000   0.5622   0.01267   0.00583  -0.0669   0.4441   0.7602
   1.250   0.5927   0.01235   0.00572  -0.0666   0.4343   1.0000
   1.500   0.6217   0.01258   0.00575  -0.0666   0.4257   1.0000
   1.750   0.6507   0.01276   0.00581  -0.0665   0.4165   1.0000
   2.000   0.6792   0.01303   0.00590  -0.0664   0.4086   1.0000
   2.250   0.7079   0.01322   0.00601  -0.0664   0.3995   1.0000
   2.500   0.7361   0.01351   0.00611  -0.0663   0.3919   1.0000
   2.750   0.7646   0.01371   0.00628  -0.0662   0.3831   1.0000
   3.000   0.7926   0.01401   0.00640  -0.0660   0.3759   1.0000
   3.250   0.8207   0.01426   0.00663  -0.0660   0.3678   1.0000
   3.500   0.8486   0.01451   0.00677  -0.0658   0.3603   1.0000
   3.750   0.8763   0.01484   0.00702  -0.0657   0.3531   1.0000
   4.000   0.9041   0.01510   0.00724  -0.0655   0.3457   1.0000
   4.250   0.9315   0.01551   0.00746  -0.0654   0.3394   1.0000
   4.500   0.9590   0.01576   0.00777  -0.0652   0.3321   1.0000
   4.750   0.9862   0.01607   0.00798  -0.0650   0.3258   1.0000
   5.000   1.0133   0.01648   0.00833  -0.0649   0.3197   1.0000
   5.250   1.0402   0.01679   0.00864  -0.0647   0.3132   1.0000
   5.500   1.0670   0.01716   0.00890  -0.0645   0.3076   1.0000
   5.750   1.0935   0.01758   0.00932  -0.0643   0.3018   1.0000
   6.000   1.1200   0.01793   0.00967  -0.0640   0.2961   1.0000
   6.250   1.1464   0.01835   0.00999  -0.0638   0.2911   1.0000
   6.500   1.1724   0.01882   0.01048  -0.0636   0.2858   1.0000
   6.750   1.1982   0.01920   0.01088  -0.0633   0.2804   1.0000
   7.000   1.2241   0.01962   0.01124  -0.0631   0.2758   1.0000
   7.250   1.2497   0.02021   0.01178  -0.0628   0.2715   1.0000
   7.500   1.2746   0.02064   0.01230  -0.0625   0.2666   1.0000
   7.750   1.2997   0.02106   0.01272  -0.0622   0.2620   1.0000
   8.000   1.3252   0.02162   0.01317  -0.0619   0.2580   1.0000
   8.250   1.3491   0.02220   0.01383  -0.0616   0.2538   1.0000
   8.500   1.3729   0.02271   0.01443  -0.0612   0.2497   1.0000
   8.750   1.3971   0.02321   0.01491  -0.0608   0.2458   1.0000
   9.000   1.4221   0.02386   0.01545  -0.0605   0.2422   1.0000
   9.250   1.4439   0.02451   0.01623  -0.0600   0.2384   1.0000
   9.500   1.4657   0.02509   0.01692  -0.0594   0.2345   1.0000
   9.750   1.4885   0.02566   0.01749  -0.0589   0.2311   1.0000
  10.000   1.5122   0.02630   0.01808  -0.0586   0.2280   1.0000
  10.250   1.5339   0.02717   0.01898  -0.0581   0.2248   1.0000
  10.500   1.5522   0.02790   0.01988  -0.0572   0.2214   1.0000
  10.750   1.5719   0.02857   0.02062  -0.0565   0.2181   1.0000
  11.000   1.5932   0.02920   0.02124  -0.0560   0.2151   1.0000
  11.250   1.6175   0.03004   0.02199  -0.0558   0.2123   1.0000
  11.500   1.6330   0.03106   0.02318  -0.0548   0.2097   1.0000
  11.750   1.6462   0.03204   0.02433  -0.0535   0.2070   1.0000
  12.000   1.6610   0.03292   0.02531  -0.0525   0.2042   1.0000
  12.250   1.6781   0.03369   0.02610  -0.0516   0.2016   1.0000
  12.500   1.6996   0.03444   0.02680  -0.0511   0.1991   1.0000
  12.750   1.7173   0.03569   0.02809  -0.0505   0.1967   1.0000
  13.000   1.7163   0.03703   0.02966  -0.0480   0.1948   1.0000
  13.250   1.7158   0.03850   0.03130  -0.0459   0.1927   1.0000
  13.500   1.7188   0.03997   0.03290  -0.0444   0.1907   1.0000
  13.750   1.7266   0.04126   0.03426  -0.0434   0.1886   1.0000
  14.000   1.7422   0.04220   0.03519  -0.0427   0.1865   1.0000
  14.250   1.7720   0.04301   0.03590  -0.0429   0.1840   1.0000
  14.500   1.7608   0.04549   0.03861  -0.0413   0.1826   1.0000
  14.750   1.7460   0.04851   0.04187  -0.0404   0.1811   1.0000
  15.000   1.7308   0.05197   0.04556  -0.0400   0.1793   1.0000
  15.250   1.7177   0.05553   0.04931  -0.0401   0.1776   1.0000
  15.500   1.7114   0.05869   0.05260  -0.0403   0.1758   1.0000
  15.750   1.7176   0.06067   0.05463  -0.0404   0.1740   1.0000
  16.000   1.7443   0.06076   0.05466  -0.0397   0.1721   1.0000
  16.250   1.7529   0.06306   0.05700  -0.0397   0.1703   1.0000
  16.500   1.6866   0.07311   0.06746  -0.0431   0.1691   1.0000
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