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MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 84 13.69% (mh84-il)
Reynolds number: 50,000
Max Cl/Cd: 30.06 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh84-il-50000-n5.txt
Download as CSV file: xf-mh84-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2383   0.10831   0.10216  -0.0170   1.0000   0.0638
  -8.750  -0.2311   0.10465   0.09859  -0.0190   1.0000   0.0614
  -8.500  -0.2322   0.10010   0.09414  -0.0227   1.0000   0.0579
  -8.250  -0.2235   0.09694   0.09110  -0.0244   1.0000   0.0570
  -8.000  -0.2185   0.09360   0.08788  -0.0265   1.0000   0.0562
  -7.750  -0.2136   0.09010   0.08451  -0.0295   0.9797   0.0553
  -7.500  -0.1974   0.08493   0.07934  -0.0364   0.9413   0.0543
  -7.250  -0.1861   0.07963   0.07401  -0.0429   0.9136   0.0535
  -7.000  -0.1799   0.07509   0.06944  -0.0476   0.8892   0.0534
  -6.750  -0.1747   0.07045   0.06476  -0.0524   0.8680   0.0535
  -6.500  -0.1813   0.05934   0.05341  -0.0658   0.8505   0.0521
  -6.250  -0.1702   0.05597   0.04994  -0.0684   0.8336   0.0530
  -6.000  -0.1603   0.05107   0.04476  -0.0728   0.8188   0.0540
  -5.750  -0.1471   0.04606   0.03933  -0.0771   0.8039   0.0552
  -5.500  -0.1296   0.04131   0.03398  -0.0804   0.7899   0.0566
  -5.250  -0.1082   0.03723   0.02914  -0.0823   0.7776   0.0582
  -5.000  -0.0853   0.03569   0.02744  -0.0822   0.7639   0.0609
  -4.750  -0.0604   0.03349   0.02471  -0.0826   0.7504   0.0653
  -4.500  -0.0362   0.03230   0.02342  -0.0820   0.7385   0.0696
  -4.250  -0.0105   0.03085   0.02167  -0.0818   0.7252   0.0755
  -4.000   0.0154   0.02970   0.02029  -0.0814   0.7127   0.0836
  -3.750   0.0411   0.02875   0.01919  -0.0807   0.7014   0.0941
  -3.500   0.0673   0.02802   0.01843  -0.0804   0.6881   0.1081
  -3.250   0.0939   0.02730   0.01756  -0.0798   0.6771   0.1279
  -3.000   0.1203   0.02682   0.01712  -0.0794   0.6645   0.1510
  -2.750   0.1474   0.02647   0.01665  -0.0790   0.6527   0.1789
  -2.500   0.1737   0.02619   0.01633  -0.0783   0.6418   0.2058
  -2.250   0.2008   0.02596   0.01596  -0.0779   0.6293   0.2336
  -2.000   0.2273   0.02562   0.01554  -0.0770   0.6198   0.2585
  -1.750   0.2546   0.02546   0.01535  -0.0767   0.6068   0.2840
  -1.500   0.2821   0.02523   0.01498  -0.0761   0.5966   0.3106
  -1.250   0.3093   0.02505   0.01474  -0.0756   0.5851   0.3374
  -1.000   0.3363   0.02489   0.01458  -0.0751   0.5743   0.3656
  -0.750   0.3634   0.02471   0.01434  -0.0745   0.5640   0.3978
  -0.500   0.3899   0.02462   0.01430  -0.0739   0.5529   0.4332
  -0.250   0.4164   0.02440   0.01411  -0.0730   0.5435   0.4762
   0.000   0.4415   0.02433   0.01423  -0.0723   0.5324   0.5283
   0.250   0.4656   0.02403   0.01407  -0.0707   0.5238   0.6003
   0.500   0.4859   0.02384   0.01424  -0.0687   0.5131   0.7023
   0.750   0.5150   0.02326   0.01382  -0.0674   0.5045   1.0000
   1.000   0.5433   0.02373   0.01404  -0.0678   0.4931   1.0000
   1.250   0.5720   0.02394   0.01388  -0.0675   0.4851   1.0000
   1.500   0.5989   0.02449   0.01427  -0.0676   0.4741   1.0000
   1.750   0.6270   0.02471   0.01418  -0.0672   0.4664   1.0000
   2.000   0.6531   0.02531   0.01468  -0.0672   0.4556   1.0000
   2.250   0.6809   0.02558   0.01468  -0.0667   0.4482   1.0000
   2.500   0.7064   0.02624   0.01527  -0.0667   0.4381   1.0000
   2.750   0.7336   0.02654   0.01534  -0.0662   0.4305   1.0000
   3.000   0.7587   0.02724   0.01598  -0.0661   0.4212   1.0000
   3.250   0.7852   0.02765   0.01623  -0.0657   0.4137   1.0000
   3.500   0.8103   0.02830   0.01679  -0.0654   0.4055   1.0000
   3.750   0.8355   0.02887   0.01728  -0.0651   0.3975   1.0000
   4.000   0.8620   0.02932   0.01755  -0.0646   0.3911   1.0000
   4.250   0.8847   0.03024   0.01852  -0.0644   0.3824   1.0000
   4.500   0.9112   0.03062   0.01873  -0.0639   0.3764   1.0000
   4.750   0.9331   0.03163   0.01978  -0.0637   0.3685   1.0000
   5.000   0.9572   0.03231   0.02042  -0.0633   0.3618   1.0000
   5.250   0.9837   0.03272   0.02066  -0.0628   0.3566   1.0000
   5.500   1.0017   0.03411   0.02220  -0.0625   0.3485   1.0000
   5.750   1.0264   0.03468   0.02269  -0.0620   0.3428   1.0000
   6.000   1.0487   0.03557   0.02355  -0.0615   0.3372   1.0000
   6.250   1.0656   0.03700   0.02509  -0.0611   0.3303   1.0000
   6.500   1.0901   0.03756   0.02557  -0.0606   0.3252   1.0000
   6.750   1.1095   0.03870   0.02675  -0.0601   0.3199   1.0000
   7.000   1.1216   0.04052   0.02872  -0.0595   0.3135   1.0000
   7.250   1.1443   0.04124   0.02939  -0.0589   0.3088   1.0000
   7.500   1.1671   0.04200   0.03008  -0.0584   0.3047   1.0000
   7.750   1.1643   0.04507   0.03344  -0.0576   0.2981   1.0000
   8.000   1.1802   0.04633   0.03474  -0.0569   0.2935   1.0000
   8.250   1.2089   0.04650   0.03479  -0.0563   0.2901   1.0000
   8.500   1.1837   0.05139   0.04002  -0.0554   0.2842   1.0000
   8.750   1.1498   0.05692   0.04573  -0.0549   0.2786   1.0000
   9.000   1.1750   0.05716   0.04593  -0.0540   0.2753   1.0000
   9.250   1.2252   0.05534   0.04399  -0.0530   0.2730   1.0000
   9.500   0.9793   0.09249   0.08178  -0.0690   0.2524   1.0000
   9.750   1.0721   0.08059   0.06974  -0.0613   0.2570   1.0000
  10.250   1.0016   0.10101   0.09036  -0.0700   0.2419   1.0000
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