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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.15 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh82-il-1000000-n5.txt
Download as CSV file: xf-mh82-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6855   0.03988   0.03675  -0.0255   0.6093   0.0052
  -9.250  -0.6985   0.03270   0.02905  -0.0262   0.6030   0.0052
  -8.750  -0.6699   0.02785   0.02363  -0.0254   0.5823   0.0053
  -8.500  -0.6544   0.02532   0.02077  -0.0248   0.5723   0.0053
  -8.250  -0.6368   0.02304   0.01816  -0.0242   0.5619   0.0053
  -8.000  -0.6149   0.02165   0.01653  -0.0236   0.5519   0.0053
  -7.750  -0.5927   0.02018   0.01482  -0.0230   0.5413   0.0053
  -7.500  -0.5691   0.01897   0.01340  -0.0225   0.5314   0.0053
  -7.250  -0.5448   0.01789   0.01212  -0.0220   0.5215   0.0053
  -7.000  -0.5198   0.01694   0.01099  -0.0216   0.5117   0.0053
  -6.750  -0.4942   0.01609   0.00997  -0.0211   0.5027   0.0053
  -6.500  -0.4683   0.01529   0.00902  -0.0207   0.4924   0.0054
  -6.250  -0.4419   0.01464   0.00824  -0.0203   0.4836   0.0054
  -6.000  -0.4153   0.01400   0.00748  -0.0200   0.4741   0.0054
  -5.750  -0.3882   0.01348   0.00686  -0.0196   0.4653   0.0055
  -5.500  -0.3610   0.01301   0.00628  -0.0193   0.4558   0.0055
  -5.250  -0.3335   0.01257   0.00576  -0.0190   0.4485   0.0056
  -5.000  -0.3058   0.01220   0.00531  -0.0188   0.4401   0.0057
  -4.750  -0.2779   0.01187   0.00492  -0.0185   0.4321   0.0057
  -4.500  -0.2499   0.01159   0.00456  -0.0183   0.4232   0.0058
  -4.250  -0.2217   0.01132   0.00423  -0.0181   0.4160   0.0060
  -4.000  -0.1934   0.01108   0.00394  -0.0179   0.4085   0.0061
  -3.750  -0.1651   0.01086   0.00366  -0.0178   0.4020   0.0062
  -3.500  -0.1366   0.01066   0.00341  -0.0176   0.3949   0.0064
  -3.250  -0.1082   0.01049   0.00318  -0.0175   0.3874   0.0067
  -3.000  -0.0796   0.01032   0.00297  -0.0173   0.3803   0.0070
  -2.750  -0.0509   0.01020   0.00279  -0.0172   0.3730   0.0073
  -2.500  -0.0224   0.01002   0.00259  -0.0171   0.3676   0.0081
  -2.250   0.0064   0.00991   0.00245  -0.0170   0.3613   0.0089
  -2.000   0.0351   0.00982   0.00232  -0.0169   0.3553   0.0100
  -1.750   0.0639   0.00971   0.00220  -0.0168   0.3497   0.0119
  -1.500   0.0926   0.00963   0.00209  -0.0167   0.3430   0.0155
  -1.250   0.1213   0.00954   0.00201  -0.0167   0.3373   0.0226
  -1.000   0.1500   0.00941   0.00192  -0.0166   0.3322   0.0385
  -0.750   0.1783   0.00922   0.00184  -0.0166   0.3268   0.0741
  -0.500   0.2066   0.00904   0.00180  -0.0165   0.3223   0.1195
  -0.250   0.2351   0.00889   0.00177  -0.0165   0.3175   0.1625
   0.000   0.2631   0.00867   0.00175  -0.0165   0.3121   0.2357
   0.250   0.2911   0.00846   0.00174  -0.0165   0.3072   0.3130
   0.500   0.3192   0.00825   0.00174  -0.0165   0.3033   0.3920
   0.750   0.3471   0.00806   0.00175  -0.0165   0.2990   0.4703
   1.000   0.3749   0.00789   0.00178  -0.0164   0.2948   0.5533
   1.250   0.4024   0.00769   0.00181  -0.0162   0.2912   0.6419
   1.500   0.4291   0.00745   0.00185  -0.0158   0.2876   0.7380
   1.750   0.4548   0.00729   0.00192  -0.0151   0.2834   0.8237
   2.000   0.4807   0.00726   0.00201  -0.0144   0.2795   0.8769
   2.250   0.5071   0.00729   0.00208  -0.0138   0.2765   0.9101
   2.500   0.5333   0.00731   0.00215  -0.0130   0.2739   0.9426
   2.750   0.5645   0.00738   0.00221  -0.0134   0.2705   0.9685
   3.000   0.6004   0.00749   0.00228  -0.0149   0.2663   0.9831
   3.250   0.6386   0.00762   0.00236  -0.0170   0.2624   0.9912
   3.500   0.6764   0.00770   0.00242  -0.0190   0.2601   0.9967
   3.750   0.7116   0.00780   0.00249  -0.0205   0.2573   1.0000
   4.000   0.7376   0.00792   0.00258  -0.0201   0.2543   1.0000
   4.250   0.7638   0.00806   0.00268  -0.0197   0.2511   1.0000
   4.500   0.7901   0.00821   0.00280  -0.0193   0.2478   1.0000
   4.750   0.8169   0.00831   0.00290  -0.0190   0.2461   1.0000
   5.000   0.8439   0.00843   0.00300  -0.0188   0.2440   1.0000
   5.250   0.8710   0.00856   0.00312  -0.0186   0.2414   1.0000
   5.500   0.8982   0.00871   0.00324  -0.0185   0.2384   1.0000
   5.750   0.9254   0.00887   0.00339  -0.0184   0.2355   1.0000
   6.000   0.9527   0.00903   0.00353  -0.0183   0.2331   1.0000
   6.250   0.9802   0.00916   0.00367  -0.0183   0.2314   1.0000
   6.500   1.0078   0.00930   0.00381  -0.0183   0.2292   1.0000
   6.750   1.0352   0.00945   0.00397  -0.0182   0.2264   1.0000
   7.000   1.0626   0.00963   0.00413  -0.0182   0.2239   1.0000
   7.250   1.0898   0.00982   0.00431  -0.0182   0.2213   1.0000
   7.500   1.1170   0.01001   0.00450  -0.0182   0.2189   1.0000
   7.750   1.1444   0.01016   0.00467  -0.0182   0.2170   1.0000
   8.000   1.1717   0.01032   0.00485  -0.0183   0.2146   1.0000
   8.250   1.1988   0.01051   0.00505  -0.0183   0.2121   1.0000
   8.500   1.2256   0.01072   0.00526  -0.0183   0.2096   1.0000
   8.750   1.2522   0.01097   0.00550  -0.0183   0.2065   1.0000
   9.000   1.2790   0.01116   0.00572  -0.0183   0.2044   1.0000
   9.250   1.3058   0.01135   0.00594  -0.0183   0.2022   1.0000
   9.500   1.3323   0.01157   0.00618  -0.0183   0.1994   1.0000
   9.750   1.3584   0.01182   0.00644  -0.0182   0.1963   1.0000
  10.000   1.3840   0.01212   0.00673  -0.0182   0.1930   1.0000
  10.250   1.4101   0.01234   0.00700  -0.0181   0.1907   1.0000
  10.500   1.4359   0.01259   0.00727  -0.0181   0.1878   1.0000
  10.750   1.4611   0.01288   0.00757  -0.0180   0.1844   1.0000
  11.000   1.4855   0.01323   0.00793  -0.0179   0.1807   1.0000
  11.250   1.5104   0.01351   0.00825  -0.0177   0.1780   1.0000
  11.500   1.5350   0.01381   0.00858  -0.0176   0.1746   1.0000
  11.750   1.5586   0.01418   0.00896  -0.0174   0.1708   1.0000
  12.000   1.5812   0.01461   0.00940  -0.0171   0.1671   1.0000
  12.250   1.6046   0.01494   0.00978  -0.0168   0.1640   1.0000
  12.500   1.6267   0.01535   0.01021  -0.0164   0.1601   1.0000
  12.750   1.6468   0.01588   0.01075  -0.0159   0.1557   1.0000
  13.000   1.6676   0.01632   0.01123  -0.0154   0.1525   1.0000
  13.250   1.6869   0.01682   0.01176  -0.0148   0.1485   1.0000
  13.500   1.7027   0.01749   0.01245  -0.0138   0.1440   1.0000
  13.750   1.7177   0.01810   0.01310  -0.0127   0.1401   1.0000
  14.000   1.7235   0.01893   0.01395  -0.0105   0.1353   1.0000
  14.250   1.7258   0.02012   0.01517  -0.0085   0.1311   1.0000
  14.500   1.7309   0.02141   0.01650  -0.0074   0.1261   1.0000
  14.750   1.7292   0.02341   0.01851  -0.0064   0.1200   1.0000
  15.000   1.7281   0.02562   0.02075  -0.0059   0.1130   1.0000
  15.250   1.7232   0.02835   0.02352  -0.0058   0.1072   1.0000
  15.500   1.7173   0.03134   0.02654  -0.0059   0.1018   1.0000
  15.750   1.7099   0.03463   0.02989  -0.0062   0.0980   1.0000
  16.000   1.7040   0.03787   0.03320  -0.0067   0.0949   1.0000
  16.250   1.6907   0.04199   0.03739  -0.0075   0.0913   1.0000
  16.500   1.6582   0.04838   0.04382  -0.0090   0.0829   1.0000
  16.750   1.6578   0.05129   0.04684  -0.0097   0.0844   1.0000
  17.000   1.6235   0.05840   0.05400  -0.0119   0.0785   1.0000
  17.250   1.6139   0.06271   0.05842  -0.0133   0.0782   1.0000
  17.500   1.5874   0.06937   0.06515  -0.0156   0.0735   1.0000
  17.750   1.5593   0.07651   0.07236  -0.0184   0.0701   1.0000
  18.000   1.5462   0.08170   0.07765  -0.0204   0.0688   1.0000
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