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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 500,000
Max Cl/Cd: 72.3 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh64-il-500000-n5.txt
Download as CSV file: xf-mh64-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 64  8.59%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5774   0.10585   0.10370   0.0172   1.0000   0.0089
  -9.500  -0.5772   0.10117   0.09904   0.0150   1.0000   0.0084
  -9.250  -0.5774   0.09640   0.09429   0.0126   1.0000   0.0080
  -9.000  -0.5786   0.09147   0.08939   0.0099   1.0000   0.0076
  -8.750  -0.5867   0.08349   0.08147   0.0063   1.0000   0.0051
  -8.500  -0.5926   0.07807   0.07608   0.0029   1.0000   0.0050
  -8.250  -0.6015   0.07224   0.07031  -0.0012   1.0000   0.0049
  -8.000  -0.6119   0.06547   0.06356  -0.0080   1.0000   0.0049
  -7.750  -0.6176   0.05528   0.05323  -0.0164   1.0000   0.0048
  -7.500  -0.6199   0.04751   0.04522  -0.0201   1.0000   0.0046
  -7.250  -0.6171   0.04076   0.03814  -0.0220   1.0000   0.0044
  -7.000  -0.6070   0.03434   0.03126  -0.0232   0.9705   0.0041
  -6.750  -0.5944   0.02829   0.02457  -0.0229   0.9327   0.0038
  -6.500  -0.5822   0.02322   0.01877  -0.0208   0.9115   0.0035
  -6.250  -0.5632   0.02040   0.01545  -0.0193   0.8964   0.0033
  -6.000  -0.5412   0.01852   0.01320  -0.0182   0.8835   0.0032
  -5.750  -0.5179   0.01709   0.01144  -0.0173   0.8720   0.0032
  -5.500  -0.4938   0.01587   0.00999  -0.0165   0.8612   0.0032
  -5.250  -0.4691   0.01479   0.00871  -0.0158   0.8508   0.0031
  -5.000  -0.4442   0.01380   0.00755  -0.0152   0.8409   0.0032
  -4.750  -0.4189   0.01296   0.00655  -0.0146   0.8314   0.0032
  -4.500  -0.3931   0.01224   0.00569  -0.0141   0.8217   0.0033
  -4.250  -0.3669   0.01160   0.00492  -0.0137   0.8122   0.0034
  -4.000  -0.3404   0.01111   0.00430  -0.0133   0.8031   0.0035
  -3.750  -0.3135   0.01069   0.00374  -0.0129   0.7938   0.0038
  -3.500  -0.2862   0.01035   0.00328  -0.0127   0.7844   0.0042
  -3.250  -0.2588   0.01007   0.00289  -0.0124   0.7753   0.0050
  -3.000  -0.2316   0.00972   0.00251  -0.0121   0.7659   0.0130
  -2.750  -0.2052   0.00915   0.00218  -0.0119   0.7562   0.0691
  -2.500  -0.1797   0.00844   0.00193  -0.0118   0.7468   0.1822
  -2.250  -0.1528   0.00815   0.00175  -0.0116   0.7373   0.2347
  -2.000  -0.1258   0.00785   0.00162  -0.0115   0.7272   0.2950
  -1.750  -0.0985   0.00762   0.00151  -0.0114   0.7172   0.3415
  -1.500  -0.0711   0.00746   0.00141  -0.0112   0.7069   0.3813
  -1.250  -0.0438   0.00731   0.00132  -0.0111   0.6962   0.4204
  -1.000  -0.0163   0.00717   0.00124  -0.0110   0.6846   0.4593
  -0.750   0.0110   0.00703   0.00117  -0.0108   0.6725   0.4999
  -0.500   0.0382   0.00689   0.00113  -0.0106   0.6598   0.5430
  -0.250   0.0651   0.00675   0.00109  -0.0103   0.6464   0.5900
   0.000   0.0917   0.00660   0.00105  -0.0100   0.6323   0.6430
   0.250   0.1178   0.00644   0.00104  -0.0095   0.6172   0.7023
   0.500   0.1430   0.00626   0.00104  -0.0088   0.6013   0.7696
   0.750   0.1676   0.00607   0.00105  -0.0078   0.5841   0.8457
   1.000   0.2012   0.00599   0.00108  -0.0086   0.5636   0.9275
   1.250   0.2488   0.00607   0.00109  -0.0129   0.5387   0.9747
   1.500   0.2863   0.00620   0.00111  -0.0150   0.5142   0.9955
   1.750   0.3165   0.00635   0.00116  -0.0155   0.4902   1.0000
   2.000   0.3431   0.00651   0.00121  -0.0153   0.4662   1.0000
   2.250   0.3697   0.00667   0.00127  -0.0150   0.4421   1.0000
   2.500   0.3963   0.00686   0.00135  -0.0148   0.4178   1.0000
   2.750   0.4229   0.00704   0.00146  -0.0146   0.3951   1.0000
   3.000   0.4496   0.00724   0.00157  -0.0144   0.3725   1.0000
   3.250   0.4763   0.00743   0.00169  -0.0142   0.3507   1.0000
   3.500   0.5029   0.00765   0.00183  -0.0141   0.3286   1.0000
   3.750   0.5297   0.00786   0.00199  -0.0139   0.3077   1.0000
   4.000   0.5563   0.00811   0.00216  -0.0137   0.2854   1.0000
   4.250   0.5828   0.00836   0.00234  -0.0136   0.2634   1.0000
   4.500   0.6093   0.00862   0.00253  -0.0134   0.2414   1.0000
   4.750   0.6357   0.00891   0.00275  -0.0133   0.2203   1.0000
   5.000   0.6621   0.00921   0.00301  -0.0131   0.1976   1.0000
   5.250   0.6883   0.00953   0.00327  -0.0130   0.1762   1.0000
   5.500   0.7143   0.00988   0.00355  -0.0128   0.1552   1.0000
   5.750   0.7402   0.01024   0.00386  -0.0126   0.1348   1.0000
   6.000   0.7661   0.01062   0.00418  -0.0124   0.1172   1.0000
   6.250   0.7915   0.01106   0.00454  -0.0122   0.0962   1.0000
   6.500   0.8167   0.01154   0.00494  -0.0120   0.0764   1.0000
   6.750   0.8420   0.01198   0.00538  -0.0118   0.0624   1.0000
   7.000   0.8670   0.01246   0.00583  -0.0115   0.0489   1.0000
   7.250   0.8908   0.01313   0.00639  -0.0112   0.0298   1.0000
   7.500   0.9146   0.01378   0.00698  -0.0109   0.0173   1.0000
   7.750   0.9385   0.01439   0.00758  -0.0105   0.0111   1.0000
   8.000   0.9626   0.01494   0.00817  -0.0101   0.0082   1.0000
   8.250   0.9858   0.01563   0.00891  -0.0097   0.0050   1.0000
   8.500   1.0083   0.01643   0.00977  -0.0091   0.0034   1.0000
   8.750   1.0300   0.01733   0.01080  -0.0084   0.0028   1.0000
   9.000   1.0515   0.01819   0.01185  -0.0078   0.0025   1.0000
   9.250   1.0721   0.01914   0.01293  -0.0070   0.0023   1.0000
   9.500   1.0916   0.02015   0.01408  -0.0062   0.0022   1.0000
   9.750   1.1098   0.02128   0.01536  -0.0053   0.0021   1.0000
  10.000   1.1265   0.02248   0.01672  -0.0043   0.0020   1.0000
  10.250   1.1412   0.02385   0.01824  -0.0031   0.0019   1.0000
  10.500   1.1540   0.02528   0.01983  -0.0018   0.0019   1.0000
  10.750   1.1646   0.02679   0.02151  -0.0003   0.0019   1.0000
  11.000   1.1716   0.02847   0.02336   0.0014   0.0018   1.0000
  11.250   1.1725   0.03012   0.02516   0.0039   0.0018   1.0000
  11.500   1.1704   0.03208   0.02729   0.0059   0.0018   1.0000
  11.750   1.1669   0.03448   0.02987   0.0072   0.0018   1.0000
  12.000   1.1626   0.03726   0.03282   0.0077   0.0018   1.0000
  12.250   1.1574   0.04040   0.03617   0.0077   0.0018   1.0000
  12.500   1.1522   0.04383   0.03977   0.0069   0.0018   1.0000
  12.750   1.1439   0.04798   0.04410   0.0055   0.0018   1.0000
  13.000   1.1343   0.05269   0.04898   0.0034   0.0017   1.0000
  13.250   1.1254   0.05767   0.05411   0.0007   0.0017   1.0000
  13.500   1.1090   0.06429   0.06092  -0.0030   0.0017   1.0000
  13.750   1.0944   0.07101   0.06780  -0.0069   0.0018   1.0000
  14.000   1.0777   0.07846   0.07540  -0.0113   0.0018   1.0000
  14.250   1.0644   0.08552   0.08258  -0.0155   0.0017   1.0000
  14.500   1.0388   0.09552   0.09276  -0.0212   0.0018   1.0000
  14.750   1.0167   0.10521   0.10256  -0.0266   0.0018   1.0000
  15.000   0.9977   0.11460   0.11206  -0.0317   0.0019   1.0000
  15.250   0.9784   0.12443   0.12200  -0.0370   0.0019   1.0000
  15.500   0.9559   0.13561   0.13329  -0.0428   0.0020   1.0000
  15.750   0.9316   0.14801   0.14579  -0.0491   0.0020   1.0000
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