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MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 61 10.26% (mh61-il)
Reynolds number: 50,000
Max Cl/Cd: 31.28 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh61-il-50000.txt
Download as CSV file: xf-mh61-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 61  10.26%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5321   0.11783   0.11180   0.0194   1.0000   0.2361
  -9.250  -0.5262   0.11367   0.10769   0.0184   1.0000   0.2427
  -9.000  -0.5404   0.11186   0.10599   0.0155   1.0000   0.2523
  -8.750  -0.5214   0.10683   0.10097   0.0161   1.0000   0.2643
  -8.500  -0.5094   0.10247   0.09665   0.0159   1.0000   0.2740
  -8.000  -0.4756   0.07656   0.07134  -0.0122   1.0000   0.1461
  -7.750  -0.5019   0.06717   0.06198  -0.0206   1.0000   0.1198
  -7.500  -0.5127   0.06024   0.05498  -0.0242   1.0000   0.1096
  -7.250  -0.5903   0.06288   0.05668  -0.0266   1.0000   0.1029
  -7.000  -0.5756   0.05770   0.05151  -0.0271   1.0000   0.0967
  -6.750  -0.5740   0.05184   0.04494  -0.0284   1.0000   0.0885
  -6.500  -0.5610   0.04739   0.04024  -0.0283   1.0000   0.0854
  -6.250  -0.5493   0.04316   0.03551  -0.0277   1.0000   0.0823
  -6.000  -0.5370   0.03967   0.03147  -0.0263   1.0000   0.0807
  -5.750  -0.5252   0.03713   0.02864  -0.0243   1.0000   0.0834
  -5.500  -0.5150   0.03493   0.02606  -0.0218   1.0000   0.0856
  -5.250  -0.5035   0.03287   0.02349  -0.0191   1.0000   0.0888
  -5.000  -0.4881   0.03053   0.02087  -0.0168   1.0000   0.0919
  -4.750  -0.4705   0.02851   0.01878  -0.0149   1.0000   0.0975
  -4.500  -0.4528   0.02669   0.01689  -0.0129   1.0000   0.1098
  -4.250  -0.4357   0.02503   0.01528  -0.0108   1.0000   0.1331
  -4.000  -0.4197   0.02281   0.01363  -0.0086   1.0000   0.2029
  -3.750  -0.4211   0.02040   0.01297  -0.0030   1.0000   0.4574
  -3.500  -0.4190   0.02014   0.01312   0.0028   1.0000   0.5685
  -3.250  -0.4128   0.01992   0.01314   0.0085   1.0000   0.6566
  -3.000  -0.4012   0.01961   0.01302   0.0133   1.0000   0.7382
  -2.750  -0.3737   0.01948   0.01298   0.0161   1.0000   0.8366
  -2.500  -0.1210   0.02057   0.01252  -0.0208   1.0000   0.9904
  -2.250  -0.1285   0.01980   0.01160  -0.0202   1.0000   1.0000
  -2.000  -0.1511   0.01941   0.01107  -0.0152   1.0000   1.0000
  -1.750  -0.1540   0.01935   0.01076  -0.0121   1.0000   1.0000
  -1.500  -0.1491   0.01946   0.01060  -0.0099   1.0000   1.0000
  -1.250  -0.1409   0.01965   0.01055  -0.0081   1.0000   1.0000
  -1.000  -0.1305   0.01991   0.01059  -0.0065   1.0000   1.0000
  -0.750  -0.1186   0.02023   0.01069  -0.0052   1.0000   1.0000
  -0.500  -0.0772   0.02095   0.01114  -0.0094   0.9902   1.0000
  -0.250  -0.0300   0.02180   0.01178  -0.0147   0.9777   1.0000
   0.000   0.0153   0.02264   0.01245  -0.0194   0.9647   1.0000
   0.250   0.0587   0.02348   0.01313  -0.0237   0.9515   1.0000
   0.500   0.1004   0.02430   0.01386  -0.0275   0.9377   1.0000
   0.750   0.1403   0.02512   0.01461  -0.0309   0.9237   1.0000
   1.000   0.1787   0.02594   0.01539  -0.0339   0.9093   1.0000
   1.250   0.2159   0.02676   0.01618  -0.0365   0.8946   1.0000
   1.500   0.2531   0.02757   0.01700  -0.0390   0.8797   1.0000
   1.750   0.2917   0.02838   0.01783  -0.0416   0.8646   1.0000
   2.000   0.3315   0.02915   0.01867  -0.0442   0.8495   1.0000
   2.250   0.3689   0.02989   0.01947  -0.0461   0.8343   1.0000
   2.500   0.3887   0.03074   0.02035  -0.0453   0.8179   1.0000
   2.750   0.4124   0.03156   0.02122  -0.0450   0.8014   1.0000
   3.000   0.4390   0.03233   0.02213  -0.0449   0.7851   1.0000
   3.250   0.4678   0.03304   0.02293  -0.0449   0.7691   1.0000
   3.500   0.4986   0.03362   0.02364  -0.0448   0.7533   1.0000
   3.750   0.5164   0.03450   0.02461  -0.0434   0.7361   1.0000
   4.000   0.5360   0.03532   0.02559  -0.0421   0.7185   1.0000
   4.250   0.5616   0.03589   0.02629  -0.0410   0.7017   1.0000
   4.500   0.5906   0.03618   0.02675  -0.0399   0.6855   1.0000
   4.750   0.6083   0.03698   0.02770  -0.0382   0.6671   1.0000
   5.000   0.6305   0.03746   0.02834  -0.0365   0.6486   1.0000
   5.250   0.6608   0.03720   0.02836  -0.0345   0.6315   1.0000
   5.500   0.6803   0.03765   0.02899  -0.0324   0.6111   1.0000
   5.750   0.7106   0.03688   0.02846  -0.0297   0.5918   1.0000
   6.000   0.7352   0.03645   0.02826  -0.0268   0.5699   1.0000
   6.250   0.7720   0.03418   0.02622  -0.0226   0.5489   1.0000
   6.500   0.8003   0.03262   0.02485  -0.0187   0.5219   1.0000
   6.750   0.8252   0.03129   0.02379  -0.0148   0.4887   1.0000
   7.000   0.8515   0.02947   0.02200  -0.0103   0.4474   1.0000
   7.250   0.8722   0.02829   0.02067  -0.0061   0.3917   1.0000
   7.500   0.8853   0.02830   0.02024  -0.0022   0.3185   1.0000
   7.750   0.8910   0.02989   0.02126   0.0011   0.2424   1.0000
   8.000   0.9001   0.03238   0.02323   0.0037   0.1858   1.0000
   8.250   0.9116   0.03491   0.02546   0.0058   0.1472   1.0000
   8.500   0.9315   0.03806   0.02852   0.0074   0.1223   1.0000
   8.750   0.9491   0.04094   0.03128   0.0087   0.1038   1.0000
   9.000   0.9662   0.04491   0.03574   0.0103   0.0959   1.0000
   9.250   0.9808   0.04865   0.03958   0.0114   0.0878   1.0000
   9.500   0.9838   0.05209   0.04358   0.0131   0.0829   1.0000
   9.750   0.9929   0.05595   0.04763   0.0143   0.0789   1.0000
  10.000   0.9967   0.06049   0.05258   0.0154   0.0778   1.0000
  10.250   0.9863   0.06470   0.05723   0.0168   0.0782   1.0000
  10.500   0.9575   0.06871   0.06168   0.0180   0.0802   1.0000
  10.750   0.9299   0.07308   0.06616   0.0181   0.0817   1.0000
  11.000   0.9030   0.07833   0.07157   0.0163   0.0832   1.0000
  11.250   0.8769   0.08455   0.07788   0.0131   0.0850   1.0000
  11.500   0.8556   0.09129   0.08467   0.0094   0.0868   1.0000
  11.750   0.8408   0.09820   0.09158   0.0059   0.0882   1.0000
  12.000   0.8334   0.10483   0.09821   0.0034   0.0892   1.0000
  12.250   0.7807   0.12485   0.11811  -0.0117   0.1148   1.0000
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