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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 200,000
Max Cl/Cd: 56.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh64-il-200000-n5.txt
Download as CSV file: xf-mh64-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5733   0.10554   0.10219   0.0153   1.0000   0.0098
  -9.500  -0.5737   0.10080   0.09744   0.0131   1.0000   0.0094
  -9.250  -0.5735   0.09616   0.09283   0.0107   1.0000   0.0092
  -9.000  -0.5739   0.09149   0.08820   0.0082   1.0000   0.0090
  -8.750  -0.5755   0.08654   0.08330   0.0053   1.0000   0.0088
  -8.500  -0.5784   0.08143   0.07823   0.0021   1.0000   0.0086
  -8.250  -0.5835   0.07591   0.07277  -0.0017   1.0000   0.0085
  -8.000  -0.5910   0.07002   0.06699  -0.0068   1.0000   0.0083
  -7.750  -0.5960   0.06151   0.05843  -0.0151   1.0000   0.0082
  -7.500  -0.5980   0.05393   0.05066  -0.0199   1.0000   0.0079
  -7.250  -0.5966   0.04728   0.04372  -0.0227   1.0000   0.0077
  -7.000  -0.5903   0.04126   0.03729  -0.0242   1.0000   0.0073
  -6.750  -0.5794   0.03576   0.03129  -0.0247   1.0000   0.0070
  -6.500  -0.5643   0.03097   0.02591  -0.0245   1.0000   0.0067
  -6.250  -0.5450   0.02734   0.02169  -0.0240   1.0000   0.0066
  -6.000  -0.5231   0.02451   0.01841  -0.0235   1.0000   0.0065
  -5.750  -0.4996   0.02224   0.01576  -0.0230   1.0000   0.0064
  -5.500  -0.4749   0.02036   0.01360  -0.0227   0.9961   0.0065
  -5.000  -0.4116   0.01722   0.00999  -0.0245   0.9513   0.0069
  -4.750  -0.3836   0.01611   0.00871  -0.0245   0.9352   0.0072
  -4.500  -0.3578   0.01522   0.00767  -0.0239   0.9204   0.0077
  -4.250  -0.3331   0.01447   0.00674  -0.0231   0.9068   0.0086
  -4.000  -0.3083   0.01387   0.00590  -0.0222   0.8942   0.0097
  -3.750  -0.2839   0.01325   0.00519  -0.0213   0.8824   0.0158
  -3.500  -0.2604   0.01230   0.00441  -0.0203   0.8712   0.0585
  -3.000  -0.2133   0.01089   0.00377  -0.0190   0.8493   0.2493
  -2.750  -0.1885   0.01051   0.00357  -0.0184   0.8387   0.3154
  -2.500  -0.1634   0.01021   0.00339  -0.0178   0.8284   0.3711
  -2.250  -0.1382   0.00996   0.00318  -0.0171   0.8185   0.4206
  -2.000  -0.1128   0.00972   0.00303  -0.0165   0.8079   0.4694
  -1.750  -0.0873   0.00948   0.00290  -0.0158   0.7972   0.5195
  -1.500  -0.0621   0.00925   0.00278  -0.0150   0.7868   0.5723
  -1.250  -0.0373   0.00901   0.00268  -0.0141   0.7765   0.6299
  -1.000  -0.0130   0.00877   0.00258  -0.0130   0.7660   0.6942
  -0.750   0.0115   0.00851   0.00253  -0.0118   0.7549   0.7671
  -0.500   0.0404   0.00831   0.00249  -0.0113   0.7438   0.8491
  -0.250   0.0848   0.00822   0.00240  -0.0142   0.7319   0.9259
   0.000   0.1291   0.00820   0.00230  -0.0175   0.7191   0.9739
   0.250   0.1685   0.00822   0.00222  -0.0199   0.7055   1.0000
   0.500   0.1941   0.00827   0.00217  -0.0193   0.6917   1.0000
   0.750   0.2197   0.00833   0.00213  -0.0188   0.6772   1.0000
   1.000   0.2456   0.00839   0.00211  -0.0183   0.6619   1.0000
   1.250   0.2715   0.00847   0.00210  -0.0178   0.6456   1.0000
   1.500   0.2974   0.00856   0.00210  -0.0173   0.6285   1.0000
   1.750   0.3236   0.00865   0.00213  -0.0168   0.6091   1.0000
   2.000   0.3497   0.00877   0.00215  -0.0164   0.5889   1.0000
   2.250   0.3760   0.00889   0.00220  -0.0160   0.5670   1.0000
   2.500   0.4022   0.00905   0.00226  -0.0156   0.5438   1.0000
   2.750   0.4284   0.00922   0.00237  -0.0152   0.5193   1.0000
   3.000   0.4546   0.00942   0.00248  -0.0149   0.4935   1.0000
   3.250   0.4808   0.00964   0.00261  -0.0146   0.4670   1.0000
   3.500   0.5070   0.00988   0.00276  -0.0143   0.4408   1.0000
   3.750   0.5332   0.01014   0.00297  -0.0140   0.4146   1.0000
   4.000   0.5593   0.01042   0.00318  -0.0137   0.3890   1.0000
   4.250   0.5854   0.01071   0.00342  -0.0135   0.3636   1.0000
   4.500   0.6113   0.01103   0.00367  -0.0132   0.3381   1.0000
   4.750   0.6372   0.01137   0.00396  -0.0130   0.3128   1.0000
   5.000   0.6630   0.01173   0.00431  -0.0128   0.2869   1.0000
   5.500   0.7140   0.01253   0.00502  -0.0123   0.2353   1.0000
   5.750   0.7393   0.01298   0.00542  -0.0120   0.2096   1.0000
   6.000   0.7643   0.01346   0.00586  -0.0118   0.1846   1.0000
   6.250   0.7890   0.01398   0.00634  -0.0115   0.1606   1.0000
   6.500   0.8134   0.01454   0.00686  -0.0112   0.1380   1.0000
   6.750   0.8376   0.01514   0.00748  -0.0109   0.1162   1.0000
   7.000   0.8615   0.01577   0.00809  -0.0106   0.0951   1.0000
   7.250   0.8846   0.01650   0.00877  -0.0102   0.0744   1.0000
   7.500   0.9075   0.01727   0.00951  -0.0098   0.0550   1.0000
   7.750   0.9295   0.01817   0.01039  -0.0092   0.0406   1.0000
   8.000   0.9503   0.01926   0.01145  -0.0086   0.0282   1.0000
   8.250   0.9709   0.02031   0.01257  -0.0079   0.0201   1.0000
   8.500   0.9911   0.02138   0.01377  -0.0072   0.0145   1.0000
   8.750   1.0080   0.02288   0.01535  -0.0062   0.0105   1.0000
   9.000   1.0275   0.02388   0.01649  -0.0055   0.0078   1.0000
   9.250   1.0427   0.02542   0.01826  -0.0044   0.0066   1.0000
   9.500   1.0515   0.02766   0.02072  -0.0028   0.0059   1.0000
   9.750   1.0637   0.02933   0.02259  -0.0015   0.0056   1.0000
  10.000   1.0733   0.03121   0.02468   0.0000   0.0053   1.0000
  10.250   1.0797   0.03332   0.02702   0.0017   0.0050   1.0000
  10.500   1.0819   0.03542   0.02933   0.0037   0.0049   1.0000
  10.750   1.0808   0.03772   0.03184   0.0055   0.0048   1.0000
  11.000   1.0777   0.04042   0.03476   0.0067   0.0047   1.0000
  11.250   1.0736   0.04339   0.03796   0.0073   0.0046   1.0000
  11.500   1.0672   0.04683   0.04162   0.0072   0.0045   1.0000
  11.750   1.0586   0.05082   0.04584   0.0064   0.0045   1.0000
  12.000   1.0481   0.05538   0.05062   0.0047   0.0044   1.0000
  12.250   1.0362   0.06054   0.05599   0.0022   0.0045   1.0000
  12.500   1.0241   0.06615   0.06179  -0.0010   0.0045   1.0000
  12.750   1.0097   0.07268   0.06851  -0.0050   0.0045   1.0000
  13.000   0.9936   0.08003   0.07604  -0.0097   0.0045   1.0000
  13.250   0.9769   0.08798   0.08414  -0.0148   0.0046   1.0000
  13.500   0.9577   0.09703   0.09334  -0.0204   0.0046   1.0000
  13.750   0.9403   0.10612   0.10255  -0.0259   0.0048   1.0000
  14.000   0.9200   0.11652   0.11305  -0.0319   0.0049   1.0000
  14.250   0.8987   0.12774   0.12434  -0.0379   0.0050   1.0000
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