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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 500,000
Max Cl/Cd: 87.09 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh82-il-500000.txt
Download as CSV file: xf-mh82-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 82  13.31%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3730   0.09480   0.09196   0.0059   0.6942   0.0201
  -8.500  -0.3705   0.09103   0.08815   0.0039   0.6812   0.0202
  -8.250  -0.3713   0.08659   0.08369   0.0012   0.6698   0.0209
  -7.750  -0.3167   0.06874   0.06588  -0.0015   0.6179   0.0226
  -7.500  -0.3173   0.06483   0.06194  -0.0032   0.6101   0.0229
  -7.250  -0.3242   0.05998   0.05710  -0.0060   0.6033   0.0230
  -7.000  -0.3410   0.05473   0.05186  -0.0102   0.5983   0.0231
  -6.750  -0.3474   0.04863   0.04566  -0.0151   0.5928   0.0234
  -6.500  -0.3493   0.04220   0.03911  -0.0188   0.5870   0.0239
  -6.250  -0.3686   0.02808   0.02431  -0.0238   0.5884   0.0262
  -6.000  -0.3502   0.02612   0.02231  -0.0238   0.5774   0.0265
  -5.750  -0.3318   0.02411   0.02022  -0.0238   0.5676   0.0271
  -5.500  -0.3170   0.02042   0.01574  -0.0233   0.5596   0.0304
  -5.250  -0.3004   0.01639   0.01164  -0.0236   0.5515   0.0311
  -5.000  -0.2780   0.01480   0.00997  -0.0235   0.5414   0.0318
  -4.750  -0.2636   0.01989   0.01339  -0.0222   0.5451   0.0172
  -4.500  -0.2363   0.01795   0.01084  -0.0212   0.5359   0.0150
  -4.250  -0.2095   0.01662   0.00937  -0.0207   0.5261   0.0149
  -4.000  -0.1824   0.01561   0.00823  -0.0203   0.5166   0.0148
  -3.750  -0.1551   0.01483   0.00731  -0.0199   0.5068   0.0148
  -3.500  -0.1274   0.01418   0.00657  -0.0195   0.4972   0.0149
  -3.250  -0.1006   0.01343   0.00573  -0.0190   0.4882   0.0152
  -3.000  -0.0734   0.01282   0.00512  -0.0187   0.4794   0.0159
  -2.750  -0.0458   0.01246   0.00468  -0.0184   0.4708   0.0168
  -2.500  -0.0176   0.01213   0.00429  -0.0181   0.4620   0.0181
  -2.250   0.0101   0.01174   0.00385  -0.0179   0.4535   0.0200
  -2.000   0.0383   0.01142   0.00351  -0.0176   0.4448   0.0233
  -1.750   0.0663   0.01113   0.00319  -0.0174   0.4370   0.0341
  -1.500   0.0933   0.01049   0.00293  -0.0172   0.4293   0.1195
  -1.250   0.1209   0.01024   0.00283  -0.0171   0.4217   0.1782
  -1.000   0.1484   0.00990   0.00275  -0.0170   0.4143   0.2564
  -0.750   0.1748   0.00944   0.00268  -0.0169   0.4068   0.3858
  -0.500   0.1983   0.00866   0.00266  -0.0162   0.4001   0.6092
  -0.250   0.2167   0.00799   0.00276  -0.0136   0.3936   0.8359
   0.000   0.2403   0.00799   0.00286  -0.0118   0.3873   0.9209
   0.250   0.2727   0.00804   0.00288  -0.0121   0.3806   0.9565
   0.500   0.3119   0.00818   0.00288  -0.0140   0.3734   0.9745
   0.750   0.3555   0.00827   0.00288  -0.0169   0.3664   0.9850
   1.000   0.4014   0.00839   0.00286  -0.0204   0.3590   0.9919
   1.250   0.4457   0.00849   0.00286  -0.0237   0.3528   0.9982
   1.500   0.4773   0.00857   0.00287  -0.0244   0.3472   1.0000
   1.750   0.5022   0.00870   0.00291  -0.0238   0.3423   1.0000
   2.000   0.5271   0.00883   0.00298  -0.0231   0.3376   1.0000
   2.250   0.5524   0.00891   0.00303  -0.0225   0.3328   1.0000
   2.500   0.5776   0.00905   0.00310  -0.0220   0.3282   1.0000
   2.750   0.6026   0.00926   0.00321  -0.0214   0.3237   1.0000
   3.000   0.6284   0.00935   0.00330  -0.0209   0.3202   1.0000
   3.250   0.6543   0.00948   0.00339  -0.0204   0.3161   1.0000
   3.500   0.6799   0.00964   0.00350  -0.0199   0.3121   1.0000
   3.750   0.7054   0.00988   0.00366  -0.0195   0.3079   1.0000
   4.000   0.7319   0.00999   0.00378  -0.0191   0.3047   1.0000
   4.250   0.7584   0.01014   0.00391  -0.0188   0.3013   1.0000
   4.500   0.7848   0.01031   0.00405  -0.0185   0.2979   1.0000
   4.750   0.8110   0.01056   0.00423  -0.0182   0.2941   1.0000
   5.000   0.8377   0.01075   0.00441  -0.0180   0.2910   1.0000
   5.250   0.8648   0.01090   0.00457  -0.0178   0.2879   1.0000
   5.500   0.8917   0.01107   0.00475  -0.0177   0.2849   1.0000
   5.750   0.9185   0.01128   0.00493  -0.0175   0.2818   1.0000
   6.000   0.9447   0.01160   0.00517  -0.0174   0.2783   1.0000
   6.250   0.9717   0.01178   0.00540  -0.0173   0.2756   1.0000
   6.500   0.9988   0.01195   0.00560  -0.0172   0.2729   1.0000
   6.750   1.0257   0.01215   0.00581  -0.0171   0.2701   1.0000
   7.000   1.0523   0.01238   0.00603  -0.0170   0.2673   1.0000
   7.250   1.0784   0.01269   0.00630  -0.0169   0.2641   1.0000
   7.500   1.1047   0.01298   0.00661  -0.0168   0.2613   1.0000
   7.750   1.1315   0.01317   0.00686  -0.0167   0.2589   1.0000
   8.000   1.1580   0.01339   0.00712  -0.0166   0.2562   1.0000
   8.250   1.1843   0.01363   0.00737  -0.0165   0.2535   1.0000
   8.500   1.2100   0.01393   0.00765  -0.0164   0.2506   1.0000
   8.750   1.2351   0.01436   0.00806  -0.0162   0.2475   1.0000
   9.000   1.2612   0.01457   0.00836  -0.0162   0.2454   1.0000
   9.250   1.2870   0.01481   0.00867  -0.0161   0.2428   1.0000
   9.500   1.3125   0.01507   0.00896  -0.0160   0.2399   1.0000
   9.750   1.3375   0.01537   0.00928  -0.0158   0.2372   1.0000
  10.000   1.3615   0.01584   0.00972  -0.0156   0.2342   1.0000
  10.250   1.3861   0.01615   0.01011  -0.0154   0.2317   1.0000
  10.500   1.4107   0.01641   0.01047  -0.0152   0.2290   1.0000
  10.750   1.4349   0.01672   0.01083  -0.0150   0.2262   1.0000
  11.000   1.4583   0.01705   0.01119  -0.0147   0.2233   1.0000
  11.250   1.4803   0.01757   0.01169  -0.0143   0.2200   1.0000
  11.500   1.5029   0.01793   0.01216  -0.0140   0.2175   1.0000
  11.750   1.5252   0.01827   0.01259  -0.0136   0.2146   1.0000
  12.000   1.5467   0.01864   0.01303  -0.0131   0.2115   1.0000
  12.250   1.5666   0.01910   0.01351  -0.0125   0.2085   1.0000
  12.500   1.5846   0.01973   0.01415  -0.0118   0.2053   1.0000
  12.750   1.6034   0.02015   0.01471  -0.0111   0.2026   1.0000
  13.000   1.6198   0.02065   0.01530  -0.0102   0.1996   1.0000
  13.250   1.6312   0.02126   0.01596  -0.0086   0.1967   1.0000
  13.500   1.6391   0.02215   0.01685  -0.0070   0.1937   1.0000
  13.750   1.6487   0.02308   0.01788  -0.0059   0.1909   1.0000
  14.000   1.6589   0.02405   0.01898  -0.0052   0.1878   1.0000
  14.250   1.6677   0.02523   0.02023  -0.0046   0.1848   1.0000
  14.500   1.6735   0.02671   0.02174  -0.0040   0.1817   1.0000
  14.750   1.6793   0.02833   0.02342  -0.0037   0.1786   1.0000
  15.000   1.6863   0.02995   0.02518  -0.0037   0.1752   1.0000
  15.250   1.6903   0.03190   0.02720  -0.0037   0.1716   1.0000
  15.500   1.6894   0.03433   0.02965  -0.0038   0.1682   1.0000
  15.750   1.6914   0.03665   0.03210  -0.0041   0.1646   1.0000
  16.000   1.6908   0.03930   0.03485  -0.0046   0.1606   1.0000
  16.250   1.6844   0.04258   0.03815  -0.0053   0.1569   1.0000
  16.500   1.6784   0.04591   0.04158  -0.0061   0.1530   1.0000
  16.750   1.6726   0.04934   0.04512  -0.0070   0.1492   1.0000
  17.000   1.6600   0.05361   0.04942  -0.0083   0.1452   1.0000
  17.250   1.6494   0.05784   0.05373  -0.0096   0.1418   1.0000
  17.500   1.6394   0.06219   0.05819  -0.0112   0.1377   1.0000
  17.750   1.6247   0.06721   0.06326  -0.0131   0.1338   1.0000
  18.000   1.6113   0.07217   0.06827  -0.0150   0.1305   1.0000
  18.250   1.5988   0.07717   0.07340  -0.0170   0.1266   1.0000
  18.500   1.5821   0.08289   0.07916  -0.0194   0.1227   1.0000
  18.750   1.5668   0.08844   0.08477  -0.0218   0.1191   1.0000
  19.000   1.5524   0.09410   0.09054  -0.0243   0.1151   1.0000
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