Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 102 16.99% (mh102-il)
Reynolds number: 500,000
Max Cl/Cd: 91.04 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh102-il-500000-n5.txt
Download as CSV file: xf-mh102-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 102  16.99%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.7970   0.08623   0.08194  -0.0486   1.0000   0.0083
 -16.000  -0.8066   0.08138   0.07702  -0.0509   1.0000   0.0083
 -15.750  -0.8167   0.07653   0.07210  -0.0533   1.0000   0.0083
 -15.500  -0.8314   0.07124   0.06673  -0.0558   1.0000   0.0084
 -15.250  -0.8477   0.06594   0.06134  -0.0584   1.0000   0.0083
 -15.000  -0.8671   0.06028   0.05559  -0.0611   1.0000   0.0084
 -14.750  -0.8844   0.05496   0.05017  -0.0637   1.0000   0.0086
 -14.500  -0.9001   0.04985   0.04496  -0.0662   1.0000   0.0084
 -14.250  -0.9160   0.04467   0.03966  -0.0688   1.0000   0.0086
 -14.000  -0.9286   0.03984   0.03472  -0.0714   1.0000   0.0087
 -13.750  -0.9404   0.03522   0.02996  -0.0740   1.0000   0.0087
 -13.500  -0.9472   0.03168   0.02631  -0.0757   1.0000   0.0088
 -13.250  -0.9527   0.02895   0.02348  -0.0761   1.0000   0.0090
 -13.000  -0.9572   0.02698   0.02141  -0.0751   1.0000   0.0090
 -12.750  -0.9631   0.02552   0.01987  -0.0726   1.0000   0.0093
 -12.500  -0.9705   0.02453   0.01882  -0.0687   1.0000   0.0094
 -12.250  -0.9678   0.02363   0.01785  -0.0659   0.9983   0.0097
 -12.000  -0.9431   0.02242   0.01658  -0.0672   0.9894   0.0101
 -11.500  -0.8902   0.02050   0.01453  -0.0694   0.9675   0.0114
 -11.000  -0.8211   0.01872   0.01262  -0.0741   0.9345   0.0130
 -10.750  -0.7851   0.01795   0.01174  -0.0765   0.9119   0.0146
 -10.250  -0.7390   0.01685   0.01040  -0.0756   0.8617   0.0177
 -10.000  -0.7189   0.01641   0.00985  -0.0744   0.8409   0.0197
  -9.750  -0.6986   0.01597   0.00932  -0.0732   0.8225   0.0223
  -9.500  -0.6777   0.01555   0.00882  -0.0722   0.8058   0.0253
  -9.250  -0.6563   0.01515   0.00833  -0.0711   0.7902   0.0291
  -9.000  -0.6346   0.01472   0.00785  -0.0702   0.7754   0.0346
  -8.750  -0.6125   0.01428   0.00738  -0.0693   0.7617   0.0414
  -8.250  -0.5683   0.01335   0.00643  -0.0675   0.7362   0.0646
  -8.000  -0.5461   0.01282   0.00596  -0.0667   0.7248   0.0834
  -7.750  -0.5231   0.01237   0.00557  -0.0660   0.7134   0.1038
  -7.500  -0.4988   0.01204   0.00526  -0.0654   0.7015   0.1220
  -7.250  -0.4738   0.01177   0.00501  -0.0649   0.6904   0.1370
  -7.000  -0.4481   0.01158   0.00480  -0.0644   0.6798   0.1495
  -6.750  -0.4216   0.01142   0.00461  -0.0640   0.6698   0.1607
  -6.500  -0.3955   0.01128   0.00444  -0.0636   0.6593   0.1703
  -6.250  -0.3686   0.01115   0.00428  -0.0633   0.6484   0.1771
  -6.000  -0.3420   0.01105   0.00413  -0.0630   0.6384   0.1858
  -5.750  -0.3151   0.01094   0.00399  -0.0627   0.6285   0.1937
  -5.500  -0.2881   0.01084   0.00386  -0.0624   0.6196   0.2000
  -5.250  -0.2606   0.01078   0.00372  -0.0621   0.6099   0.2047
  -5.000  -0.2338   0.01068   0.00358  -0.0618   0.6006   0.2094
  -4.750  -0.2066   0.01060   0.00345  -0.0615   0.5907   0.2144
  -4.500  -0.1792   0.01055   0.00334  -0.0612   0.5819   0.2190
  -4.250  -0.1518   0.01049   0.00322  -0.0610   0.5731   0.2231
  -4.000  -0.1247   0.01041   0.00312  -0.0607   0.5653   0.2283
  -3.750  -0.0971   0.01035   0.00303  -0.0605   0.5567   0.2333
  -3.500  -0.0697   0.01033   0.00294  -0.0603   0.5483   0.2381
  -3.250  -0.0423   0.01026   0.00285  -0.0600   0.5397   0.2435
  -2.750   0.0128   0.01019   0.00272  -0.0596   0.5248   0.2545
  -2.500   0.0402   0.01015   0.00266  -0.0594   0.5174   0.2608
  -2.250   0.0676   0.01012   0.00261  -0.0592   0.5104   0.2676
  -2.000   0.0954   0.01011   0.00256  -0.0590   0.5028   0.2733
  -1.500   0.1503   0.01006   0.00250  -0.0586   0.4897   0.2888
  -1.250   0.1777   0.01004   0.00248  -0.0584   0.4830   0.2967
  -1.000   0.2050   0.01005   0.00247  -0.0581   0.4767   0.3051
  -0.750   0.2327   0.01004   0.00246  -0.0580   0.4705   0.3131
  -0.500   0.2601   0.01003   0.00246  -0.0578   0.4642   0.3232
  -0.250   0.2872   0.01004   0.00247  -0.0575   0.4585   0.3337
   0.000   0.3150   0.01004   0.00248  -0.0574   0.4526   0.3446
   0.250   0.3422   0.01004   0.00250  -0.0572   0.4467   0.3555
   0.500   0.3692   0.01008   0.00253  -0.0569   0.4412   0.3668
   0.750   0.3968   0.01007   0.00256  -0.0567   0.4361   0.3809
   1.000   0.4239   0.01007   0.00260  -0.0565   0.4306   0.3955
   1.250   0.4506   0.01011   0.00265  -0.0562   0.4252   0.4100
   1.500   0.4780   0.01012   0.00270  -0.0560   0.4206   0.4252
   1.750   0.5051   0.01012   0.00276  -0.0558   0.4154   0.4431
   2.000   0.5316   0.01014   0.00282  -0.0555   0.4104   0.4636
   2.250   0.5581   0.01017   0.00290  -0.0552   0.4057   0.4855
   2.500   0.5851   0.01016   0.00298  -0.0549   0.4012   0.5089
   3.000   0.6371   0.01019   0.00317  -0.0541   0.3913   0.5695
   3.250   0.6631   0.01018   0.00328  -0.0537   0.3871   0.6041
   3.500   0.6889   0.01016   0.00339  -0.0533   0.3822   0.6413
   3.750   0.7139   0.01017   0.00351  -0.0526   0.3771   0.6817
   4.000   0.7380   0.01020   0.00365  -0.0518   0.3724   0.7242
   4.250   0.7628   0.01016   0.00378  -0.0511   0.3677   0.7691
   4.500   0.7864   0.01016   0.00392  -0.0501   0.3625   0.8155
   4.750   0.8094   0.01020   0.00408  -0.0489   0.3572   0.8639
   5.000   0.8372   0.01025   0.00425  -0.0487   0.3521   0.9147
   5.250   0.8800   0.01040   0.00443  -0.0518   0.3454   0.9555
   5.500   0.9216   0.01062   0.00462  -0.0548   0.3384   0.9825
   5.750   0.9597   0.01079   0.00479  -0.0570   0.3318   1.0000
   6.000   0.9815   0.01097   0.00495  -0.0559   0.3251   1.0000
   6.250   1.0038   0.01116   0.00511  -0.0549   0.3190   1.0000
   6.500   1.0264   0.01134   0.00529  -0.0539   0.3120   1.0000
   6.750   1.0479   0.01157   0.00548  -0.0528   0.3052   1.0000
   7.000   1.0706   0.01176   0.00568  -0.0519   0.2980   1.0000
   7.250   1.0916   0.01203   0.00591  -0.0507   0.2906   1.0000
   7.500   1.1137   0.01225   0.00613  -0.0497   0.2833   1.0000
   7.750   1.1338   0.01255   0.00639  -0.0484   0.2752   1.0000
   8.000   1.1549   0.01281   0.00664  -0.0473   0.2679   1.0000
   8.250   1.1741   0.01313   0.00694  -0.0459   0.2601   1.0000
   8.500   1.1938   0.01343   0.00722  -0.0446   0.2534   1.0000
   8.750   1.2113   0.01376   0.00754  -0.0429   0.2459   1.0000
   9.000   1.2271   0.01410   0.00787  -0.0409   0.2395   1.0000
   9.250   1.2429   0.01444   0.00821  -0.0389   0.2327   1.0000
   9.500   1.2565   0.01488   0.00863  -0.0367   0.2265   1.0000
   9.750   1.2727   0.01524   0.00901  -0.0350   0.2201   1.0000
  10.000   1.2861   0.01573   0.00949  -0.0329   0.2138   1.0000
  10.250   1.3007   0.01620   0.00996  -0.0311   0.2078   1.0000
  10.500   1.3143   0.01672   0.01050  -0.0292   0.2016   1.0000
  10.750   1.3259   0.01735   0.01113  -0.0272   0.1962   1.0000
  11.000   1.3399   0.01792   0.01172  -0.0256   0.1906   1.0000
  11.250   1.3508   0.01865   0.01246  -0.0237   0.1850   1.0000
  11.500   1.3618   0.01943   0.01326  -0.0221   0.1798   1.0000
  11.750   1.3732   0.02024   0.01409  -0.0205   0.1742   1.0000
  12.000   1.3808   0.02130   0.01515  -0.0188   0.1688   1.0000
  12.250   1.3919   0.02222   0.01611  -0.0175   0.1642   1.0000
  12.500   1.4005   0.02335   0.01726  -0.0161   0.1589   1.0000
  12.750   1.4064   0.02472   0.01865  -0.0148   0.1542   1.0000
  13.000   1.4160   0.02591   0.01989  -0.0138   0.1499   1.0000
  13.250   1.4223   0.02738   0.02138  -0.0127   0.1451   1.0000
  13.500   1.4261   0.02912   0.02315  -0.0117   0.1409   1.0000
  13.750   1.4333   0.03064   0.02473  -0.0110   0.1369   1.0000
  14.000   1.4370   0.03251   0.02663  -0.0102   0.1324   1.0000
  14.500   1.4431   0.03654   0.03076  -0.0091   0.1252   1.0000
  14.750   1.4447   0.03878   0.03304  -0.0087   0.1211   1.0000
  15.000   1.4427   0.04143   0.03572  -0.0083   0.1173   1.0000
  15.250   1.4448   0.04374   0.03810  -0.0081   0.1143   1.0000
  15.500   1.4450   0.04632   0.04073  -0.0081   0.1104   1.0000
  15.750   1.4419   0.04930   0.04375  -0.0081   0.1070   1.0000
  16.000   1.4401   0.05221   0.04672  -0.0083   0.1041   1.0000
  16.250   1.4393   0.05508   0.04965  -0.0085   0.1004   1.0000
  16.500   1.4358   0.05832   0.05293  -0.0088   0.0972   1.0000
  16.750   1.4305   0.06183   0.05649  -0.0094   0.0944   1.0000
  17.000   1.4292   0.06493   0.05966  -0.0099   0.0914   1.0000
  17.250   1.4239   0.06856   0.06334  -0.0106   0.0879   1.0000
  17.500   1.4176   0.07239   0.06722  -0.0114   0.0854   1.0000
  17.750   1.4160   0.07566   0.07056  -0.0121   0.0829   1.0000
  18.000   1.4121   0.07930   0.07426  -0.0130   0.0803   1.0000
  18.250   1.4055   0.08335   0.07836  -0.0142   0.0775   1.0000
  18.500   1.4003   0.08725   0.08231  -0.0153   0.0751   1.0000
  18.750   1.3968   0.09099   0.08612  -0.0164   0.0726   1.0000
  19.000   1.3921   0.09492   0.09012  -0.0177   0.0703   1.0000
<< Back to MH 102 16.99% (mh102-il)

Polar data table (+)

Polar graphs


<< Back to MH 102 16.99% (mh102-il)