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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 50,000
Max Cl/Cd: 38.02 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh122-il-50000.txt
Download as CSV file: xf-mh122-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 122  9.32%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4489   0.10680   0.10070  -0.0208   1.0000   0.2489
  -7.250  -0.4447   0.10377   0.09772  -0.0183   1.0000   0.2618
  -7.000  -0.4425   0.10098   0.09499  -0.0158   1.0000   0.2743
  -6.750  -0.4433   0.09852   0.09259  -0.0133   1.0000   0.2866
  -6.500  -0.4507   0.09652   0.09068  -0.0102   1.0000   0.3001
  -6.000  -0.4655   0.09280   0.08713  -0.0040   1.0000   0.3274
  -5.750  -0.4820   0.09155   0.08601  -0.0013   1.0000   0.3433
  -5.500  -0.4741   0.08822   0.08272   0.0018   1.0000   0.3608
  -5.250  -0.4723   0.08575   0.08030   0.0047   1.0000   0.3794
  -4.250  -0.3866   0.04766   0.04000  -0.0591   1.0000   0.1118
  -4.000  -0.3517   0.04287   0.03452  -0.0619   1.0000   0.0971
  -3.750  -0.3157   0.03882   0.02962  -0.0641   1.0000   0.0883
  -3.500  -0.2833   0.03639   0.02642  -0.0648   1.0000   0.0861
  -3.250  -0.2564   0.03368   0.02363  -0.0652   1.0000   0.0931
  -3.000  -0.2266   0.03178   0.02121  -0.0651   1.0000   0.0982
  -2.750  -0.1995   0.02984   0.01909  -0.0643   1.0000   0.1027
  -2.500  -0.1742   0.02820   0.01736  -0.0632   1.0000   0.1218
  -2.250  -0.1444   0.02632   0.01561  -0.0630   1.0000   0.1646
  -2.000  -0.1293   0.02370   0.01591  -0.0569   1.0000   0.6907
  -1.750  -0.1357   0.02369   0.01604  -0.0473   1.0000   0.7837
  -1.500  -0.1427   0.02325   0.01570  -0.0382   1.0000   0.8593
  -1.250  -0.1324   0.02210   0.01458  -0.0339   1.0000   1.0000
  -1.000  -0.0915   0.02224   0.01409  -0.0393   1.0000   1.0000
  -0.750  -0.0530   0.02252   0.01383  -0.0437   1.0000   1.0000
  -0.500  -0.0185   0.02287   0.01373  -0.0468   1.0000   1.0000
  -0.250   0.0125   0.02326   0.01368  -0.0490   1.0000   1.0000
   0.000   0.0409   0.02369   0.01379  -0.0505   1.0000   1.0000
   0.250   0.0676   0.02415   0.01396  -0.0516   1.0000   1.0000
   0.500   0.0929   0.02464   0.01422  -0.0523   1.0000   1.0000
   0.750   0.1174   0.02515   0.01449  -0.0528   1.0000   1.0000
   1.000   0.1411   0.02570   0.01486  -0.0532   1.0000   1.0000
   1.250   0.1641   0.02627   0.01530  -0.0535   1.0000   1.0000
   1.500   0.1865   0.02688   0.01580  -0.0537   1.0000   1.0000
   1.750   0.2085   0.02753   0.01636  -0.0538   1.0000   1.0000
   2.000   0.2300   0.02821   0.01696  -0.0539   1.0000   1.0000
   2.250   0.2510   0.02893   0.01763  -0.0540   1.0000   1.0000
   2.500   0.2716   0.02969   0.01837  -0.0541   1.0000   1.0000
   2.750   0.2916   0.03050   0.01917  -0.0541   1.0000   1.0000
   3.000   0.3113   0.03136   0.02004  -0.0541   1.0000   1.0000
   3.250   0.3303   0.03228   0.02099  -0.0542   1.0000   1.0000
   3.500   0.3490   0.03326   0.02204  -0.0542   1.0000   1.0000
   3.750   0.3670   0.03431   0.02314  -0.0543   1.0000   1.0000
   4.000   0.3845   0.03543   0.02433  -0.0544   1.0000   1.0000
   4.250   0.4014   0.03663   0.02562  -0.0546   1.0000   1.0000
   4.500   0.4177   0.03792   0.02701  -0.0548   1.0000   1.0000
   4.750   0.4871   0.04070   0.03015  -0.0647   0.9670   1.0000
   5.000   0.5412   0.04237   0.03211  -0.0710   0.9365   1.0000
   5.250   0.5998   0.04373   0.03381  -0.0771   0.9061   1.0000
   5.500   0.6491   0.04438   0.03490  -0.0809   0.8726   1.0000
   5.750   0.7149   0.04410   0.03512  -0.0856   0.8351   1.0000
   6.000   0.7900   0.04178   0.03347  -0.0889   0.7905   1.0000
   6.250   0.8759   0.03627   0.02899  -0.0896   0.7385   1.0000
   6.500   0.9713   0.02555   0.01750  -0.0798   0.4043   1.0000
   6.750   0.9733   0.02920   0.01952  -0.0753   0.2664   1.0000
   7.000   1.0256   0.03319   0.02261  -0.0785   0.1779   1.0000
   7.250   1.0845   0.03761   0.02690  -0.0823   0.1373   1.0000
   7.500   1.1126   0.04079   0.03036  -0.0817   0.1163   1.0000
   7.750   1.1426   0.04539   0.03548  -0.0809   0.1070   1.0000
   8.000   1.1589   0.04899   0.03956  -0.0789   0.0956   1.0000
   8.250   1.1727   0.05292   0.04397  -0.0764   0.0897   1.0000
   8.500   1.1860   0.05784   0.04929  -0.0741   0.0878   1.0000
   8.750   1.1856   0.06233   0.05448  -0.0701   0.0890   1.0000
   9.000   1.1810   0.06693   0.05964  -0.0662   0.0901   1.0000
   9.250   1.1710   0.07145   0.06463  -0.0625   0.0913   1.0000
   9.500   1.1573   0.07603   0.06959  -0.0590   0.0930   1.0000
   9.750   1.1424   0.08053   0.07436  -0.0560   0.0947   1.0000
  10.000   1.1258   0.08484   0.07885  -0.0531   0.0960   1.0000
  10.250   1.1110   0.08949   0.08364  -0.0510   0.0973   1.0000
  10.500   1.1007   0.09473   0.08897  -0.0499   0.0984   1.0000
  10.750   0.9285   0.09685   0.09168  -0.0438   0.1070   1.0000
  11.000   0.9056   0.10384   0.09872  -0.0461   0.1098   1.0000
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