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MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 94 16.03% (mh94-il)
Reynolds number: 100,000
Max Cl/Cd: 40.32 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh94-il-100000.txt
Download as CSV file: xf-mh94-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 94  16.03%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5363   0.11014   0.10454  -0.0522   1.0000   0.0692
 -13.000  -0.6092   0.09137   0.08563  -0.0627   1.0000   0.0609
 -12.750  -0.6231   0.08596   0.08020  -0.0642   1.0000   0.0598
 -12.500  -0.6571   0.07906   0.07320  -0.0670   1.0000   0.0587
 -12.250  -0.6986   0.07278   0.06674  -0.0687   1.0000   0.0576
 -12.000  -0.7502   0.06722   0.06091  -0.0684   1.0000   0.0562
 -11.750  -0.8247   0.06382   0.05708  -0.0634   1.0000   0.0548
 -11.500  -0.8544   0.06227   0.05534  -0.0581   1.0000   0.0543
 -11.250  -0.8630   0.05969   0.05268  -0.0547   1.0000   0.0539
 -11.000  -0.8721   0.05717   0.05006  -0.0512   1.0000   0.0535
 -10.750  -0.8822   0.05470   0.04743  -0.0474   1.0000   0.0532
 -10.500  -0.8917   0.05224   0.04475  -0.0435   1.0000   0.0529
 -10.250  -0.8971   0.04983   0.04211  -0.0399   1.0000   0.0525
 -10.000  -0.8998   0.04747   0.03949  -0.0364   1.0000   0.0524
  -9.750  -0.8984   0.04519   0.03697  -0.0332   1.0000   0.0522
  -9.500  -0.8942   0.04303   0.03454  -0.0302   1.0000   0.0523
  -9.250  -0.8878   0.04108   0.03232  -0.0274   1.0000   0.0528
  -9.000  -0.8804   0.03935   0.03028  -0.0245   1.0000   0.0538
  -8.750  -0.8685   0.03758   0.02829  -0.0223   1.0000   0.0549
  -8.500  -0.8503   0.03605   0.02684  -0.0211   1.0000   0.0568
  -8.250  -0.8343   0.03471   0.02545  -0.0193   1.0000   0.0588
  -8.000  -0.8179   0.03336   0.02392  -0.0173   1.0000   0.0606
  -7.750  -0.7990   0.03189   0.02245  -0.0158   1.0000   0.0626
  -7.500  -0.7827   0.03070   0.02136  -0.0140   1.0000   0.0656
  -7.250  -0.7682   0.02969   0.02026  -0.0118   1.0000   0.0697
  -7.000  -0.7558   0.02853   0.01931  -0.0097   1.0000   0.0747
  -6.750  -0.7445   0.02741   0.01825  -0.0073   1.0000   0.0808
  -6.500  -0.7348   0.02626   0.01718  -0.0047   1.0000   0.0897
  -6.250  -0.7260   0.02503   0.01611  -0.0021   1.0000   0.1027
  -6.000  -0.7185   0.02349   0.01486   0.0004   1.0000   0.1305
  -5.750  -0.7178   0.02076   0.01331   0.0031   1.0000   0.2597
  -5.500  -0.7081   0.01974   0.01299   0.0054   1.0000   0.3900
  -5.250  -0.6924   0.01963   0.01307   0.0074   1.0000   0.4473
  -5.000  -0.6756   0.01975   0.01327   0.0093   1.0000   0.4877
  -4.750  -0.6582   0.01995   0.01348   0.0111   1.0000   0.5198
  -4.500  -0.6408   0.02025   0.01381   0.0131   1.0000   0.5464
  -4.250  -0.6235   0.02056   0.01408   0.0149   1.0000   0.5726
  -4.000  -0.6069   0.02104   0.01464   0.0173   1.0000   0.5947
  -3.750  -0.5884   0.02163   0.01528   0.0194   0.9992   0.6162
  -3.500  -0.5480   0.02283   0.01649   0.0176   0.9902   0.6396
  -3.250  -0.5075   0.02374   0.01735   0.0156   0.9816   0.6575
  -3.000  -0.4697   0.02426   0.01780   0.0137   0.9720   0.6729
  -2.750  -0.4348   0.02461   0.01806   0.0123   0.9620   0.6883
  -2.500  -0.3989   0.02512   0.01854   0.0111   0.9526   0.7006
  -2.250  -0.3600   0.02556   0.01894   0.0093   0.9436   0.7134
  -2.000  -0.3298   0.02565   0.01895   0.0087   0.9327   0.7274
  -1.750  -0.2948   0.02601   0.01931   0.0079   0.9231   0.7385
  -1.500  -0.2574   0.02616   0.01941   0.0063   0.9137   0.7504
  -1.250  -0.2281   0.02617   0.01937   0.0060   0.9022   0.7632
  -1.000  -0.1822   0.02637   0.01955   0.0036   0.8952   0.7728
  -0.750  -0.1570   0.02618   0.01932   0.0038   0.8822   0.7854
  -0.500  -0.1268   0.02622   0.01937   0.0041   0.8711   0.7944
  -0.250  -0.0833   0.02598   0.01909   0.0017   0.8627   0.8060
   0.000  -0.0575   0.02590   0.01901   0.0027   0.8499   0.8158
   0.250  -0.0065   0.02547   0.01856  -0.0006   0.8438   0.8261
   0.500   0.0176   0.02526   0.01835   0.0007   0.8296   0.8365
   0.750   0.0505   0.02491   0.01800   0.0005   0.8182   0.8465
   1.000   0.0982   0.02427   0.01736  -0.0018   0.8104   0.8564
   1.250   0.1321   0.02381   0.01692  -0.0019   0.7985   0.8658
   1.500   0.1904   0.02296   0.01607  -0.0059   0.7921   0.8743
   1.750   0.2313   0.02245   0.01557  -0.0072   0.7794   0.8829
   2.000   0.3082   0.02153   0.01466  -0.0145   0.7720   0.8881
   2.250   0.3474   0.02097   0.01409  -0.0157   0.7557   0.8974
   2.500   0.4067   0.02042   0.01353  -0.0204   0.7376   0.9028
   2.750   0.4486   0.01988   0.01294  -0.0221   0.7170   0.9122
   3.000   0.5002   0.01959   0.01259  -0.0257   0.6882   0.9173
   3.250   0.5451   0.01930   0.01215  -0.0282   0.6584   0.9249
   3.500   0.5846   0.01917   0.01191  -0.0300   0.6238   0.9322
   3.750   0.6191   0.01915   0.01174  -0.0310   0.5882   0.9410
   4.000   0.6587   0.01921   0.01162  -0.0332   0.5493   0.9481
   4.250   0.6879   0.01935   0.01158  -0.0336   0.5127   0.9579
   4.500   0.7269   0.01962   0.01160  -0.0360   0.4725   0.9654
   4.750   0.7599   0.01993   0.01171  -0.0375   0.4339   0.9742
   5.000   0.7929   0.02034   0.01190  -0.0391   0.3965   0.9834
   5.250   0.8286   0.02083   0.01216  -0.0414   0.3590   0.9920
   5.500   0.8637   0.02142   0.01249  -0.0438   0.3248   1.0000
   5.750   0.8660   0.02182   0.01277  -0.0399   0.3059   1.0000
   6.000   0.8679   0.02223   0.01304  -0.0359   0.2891   1.0000
   6.250   0.8676   0.02257   0.01333  -0.0315   0.2741   1.0000
   6.500   0.8670   0.02293   0.01364  -0.0270   0.2608   1.0000
   6.750   0.8675   0.02335   0.01396  -0.0227   0.2496   1.0000
   7.000   0.8687   0.02373   0.01424  -0.0185   0.2394   1.0000
   7.250   0.8754   0.02426   0.01474  -0.0152   0.2290   1.0000
   7.500   0.8937   0.02506   0.01535  -0.0141   0.2189   1.0000
   7.750   0.9106   0.02576   0.01609  -0.0126   0.2095   1.0000
   8.000   0.9362   0.02679   0.01698  -0.0127   0.2015   1.0000
   8.250   0.9560   0.02761   0.01788  -0.0117   0.1941   1.0000
   8.500   0.9870   0.02882   0.01885  -0.0128   0.1873   1.0000
   8.750   1.0039   0.02972   0.01998  -0.0113   0.1820   1.0000
   9.000   1.0269   0.03074   0.02104  -0.0109   0.1770   1.0000
   9.250   1.0588   0.03213   0.02225  -0.0122   0.1722   1.0000
   9.500   1.0747   0.03332   0.02368  -0.0106   0.1686   1.0000
   9.750   1.0919   0.03451   0.02506  -0.0094   0.1649   1.0000
  10.000   1.1117   0.03573   0.02636  -0.0086   0.1614   1.0000
  10.250   1.1374   0.03718   0.02777  -0.0089   0.1585   1.0000
  10.500   1.1577   0.03914   0.02984  -0.0085   0.1559   1.0000
  10.750   1.1634   0.04070   0.03173  -0.0058   0.1538   1.0000
  11.000   1.1697   0.04240   0.03370  -0.0033   0.1516   1.0000
  11.250   1.1775   0.04415   0.03564  -0.0012   0.1494   1.0000
  11.500   1.1873   0.04595   0.03761   0.0005   0.1475   1.0000
  11.750   1.1975   0.04783   0.03962   0.0021   0.1459   1.0000
  12.000   1.2104   0.04981   0.04166   0.0031   0.1442   1.0000
  12.250   1.2257   0.05283   0.04473   0.0033   0.1425   1.0000
  12.500   1.2054   0.05514   0.04734   0.0084   0.1419   1.0000
  12.750   1.1808   0.05793   0.05042   0.0130   0.1415   1.0000
  13.000   1.1507   0.06137   0.05414   0.0170   0.1412   1.0000
  13.250   1.1140   0.06572   0.05877   0.0199   0.1411   1.0000
  13.500   1.0704   0.07147   0.06477   0.0213   0.1414   1.0000
  13.750   1.0189   0.07927   0.07280   0.0204   0.1420   1.0000
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