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MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 200,000
Max Cl/Cd: 70.26 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh70-il-200000.txt
Download as CSV file: xf-mh70-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2862   0.08997   0.08688  -0.0274   1.0000   0.0469
  -9.000  -0.2980   0.08486   0.08182  -0.0321   1.0000   0.0487
  -8.750  -0.3107   0.07956   0.07657  -0.0372   1.0000   0.0491
  -8.500  -0.3229   0.07396   0.07104  -0.0422   1.0000   0.0493
  -8.250  -0.2976   0.07173   0.06884  -0.0360   1.0000   0.0510
  -8.000  -0.2920   0.06874   0.06589  -0.0361   1.0000   0.0523
  -7.750  -0.2945   0.06532   0.06254  -0.0370   1.0000   0.0536
  -7.500  -0.4314   0.06895   0.06581  -0.0480   0.9977   0.0492
  -7.250  -0.4086   0.06456   0.06161  -0.0481   0.9934   0.0505
  -7.000  -0.3230   0.04119   0.03786  -0.0682   0.9638   0.0597
  -6.750  -0.2938   0.03784   0.03477  -0.0681   0.9590   0.0617
  -6.500  -0.3330   0.04811   0.04458  -0.0683   0.9659   0.0615
  -6.250  -0.3031   0.04501   0.04141  -0.0714   0.9585   0.0651
  -6.000  -0.2816   0.04067   0.03669  -0.0748   0.9467   0.0738
  -5.750  -0.2670   0.02775   0.02194  -0.0739   0.9338   0.0346
  -5.500  -0.2408   0.02510   0.01895  -0.0735   0.9250   0.0320
  -5.250  -0.2178   0.02247   0.01586  -0.0723   0.9147   0.0300
  -5.000  -0.1937   0.02045   0.01336  -0.0710   0.9050   0.0289
  -4.750  -0.1686   0.01909   0.01179  -0.0699   0.8967   0.0292
  -4.500  -0.1446   0.01797   0.01058  -0.0688   0.8866   0.0300
  -4.250  -0.1202   0.01702   0.00953  -0.0676   0.8784   0.0317
  -4.000  -0.0960   0.01614   0.00855  -0.0664   0.8690   0.0339
  -3.750  -0.0721   0.01547   0.00788  -0.0655   0.8605   0.0404
  -3.500  -0.0486   0.01461   0.00702  -0.0643   0.8519   0.0492
  -3.250  -0.0254   0.01361   0.00617  -0.0633   0.8432   0.0823
  -3.000  -0.0039   0.01238   0.00568  -0.0624   0.8353   0.2367
  -2.750   0.0198   0.01190   0.00555  -0.0617   0.8263   0.3376
  -2.500   0.0438   0.01152   0.00539  -0.0607   0.8187   0.4234
  -2.250   0.0672   0.01115   0.00532  -0.0596   0.8095   0.5130
  -2.000   0.0894   0.01072   0.00522  -0.0580   0.8022   0.6178
  -1.750   0.1104   0.01037   0.00525  -0.0559   0.7927   0.7258
  -1.500   0.1324   0.01014   0.00521  -0.0534   0.7857   0.8257
  -1.250   0.1636   0.01007   0.00519  -0.0529   0.7760   0.9051
  -1.000   0.2093   0.01003   0.00501  -0.0556   0.7686   0.9546
  -0.750   0.2634   0.00999   0.00481  -0.0606   0.7586   0.9836
  -0.500   0.3156   0.00990   0.00454  -0.0655   0.7493   1.0000
  -0.250   0.3375   0.00990   0.00440  -0.0643   0.7397   1.0000
   0.000   0.3600   0.00993   0.00433  -0.0632   0.7290   1.0000
   0.250   0.3831   0.00996   0.00423  -0.0622   0.7196   1.0000
   0.500   0.4066   0.01000   0.00416  -0.0612   0.7089   1.0000
   0.750   0.4305   0.01005   0.00413  -0.0603   0.6978   1.0000
   1.000   0.4547   0.01010   0.00406  -0.0594   0.6876   1.0000
   1.250   0.4792   0.01015   0.00401  -0.0586   0.6763   1.0000
   1.500   0.5037   0.01021   0.00401  -0.0578   0.6642   1.0000
   1.750   0.5285   0.01028   0.00400  -0.0570   0.6522   1.0000
   2.000   0.5536   0.01035   0.00399  -0.0562   0.6404   1.0000
   2.250   0.5789   0.01043   0.00397  -0.0555   0.6281   1.0000
   2.500   0.6041   0.01051   0.00400  -0.0549   0.6143   1.0000
   2.750   0.6295   0.01061   0.00405  -0.0543   0.6002   1.0000
   3.000   0.6549   0.01072   0.00410  -0.0536   0.5857   1.0000
   3.250   0.6803   0.01084   0.00416  -0.0530   0.5707   1.0000
   3.500   0.7057   0.01098   0.00424  -0.0524   0.5552   1.0000
   3.750   0.7311   0.01114   0.00433  -0.0519   0.5392   1.0000
   4.000   0.7563   0.01132   0.00445  -0.0513   0.5227   1.0000
   4.250   0.7814   0.01152   0.00458  -0.0507   0.5059   1.0000
   4.500   0.8063   0.01176   0.00473  -0.0501   0.4888   1.0000
   4.750   0.8312   0.01200   0.00494  -0.0495   0.4706   1.0000
   5.000   0.8558   0.01226   0.00516  -0.0489   0.4522   1.0000
   5.250   0.8802   0.01255   0.00539  -0.0483   0.4339   1.0000
   5.500   0.9043   0.01287   0.00566  -0.0477   0.4156   1.0000
   5.750   0.9282   0.01322   0.00593  -0.0471   0.3977   1.0000
   6.000   0.9519   0.01359   0.00624  -0.0464   0.3796   1.0000
   6.250   0.9754   0.01396   0.00660  -0.0458   0.3616   1.0000
   6.500   0.9987   0.01437   0.00697  -0.0451   0.3442   1.0000
   6.750   1.0215   0.01480   0.00736  -0.0444   0.3274   1.0000
   7.000   1.0441   0.01526   0.00778  -0.0437   0.3112   1.0000
   7.250   1.0664   0.01574   0.00824  -0.0430   0.2959   1.0000
   7.500   1.0884   0.01624   0.00872  -0.0422   0.2812   1.0000
   7.750   1.1101   0.01677   0.00922  -0.0414   0.2673   1.0000
   8.000   1.1313   0.01732   0.00977  -0.0406   0.2541   1.0000
   8.250   1.1520   0.01791   0.01033  -0.0397   0.2416   1.0000
   8.500   1.1721   0.01855   0.01091  -0.0387   0.2299   1.0000
   8.750   1.1924   0.01909   0.01152  -0.0378   0.2181   1.0000
   9.000   1.2120   0.01970   0.01218  -0.0368   0.2072   1.0000
   9.250   1.2306   0.02039   0.01286  -0.0357   0.1971   1.0000
   9.500   1.2483   0.02111   0.01355  -0.0345   0.1874   1.0000
   9.750   1.2660   0.02173   0.01429  -0.0332   0.1776   1.0000
  10.000   1.2821   0.02253   0.01509  -0.0319   0.1690   1.0000
  10.250   1.2969   0.02326   0.01585  -0.0304   0.1604   1.0000
  10.500   1.3106   0.02404   0.01672  -0.0287   0.1523   1.0000
  10.750   1.3212   0.02497   0.01759  -0.0267   0.1451   1.0000
  11.000   1.3318   0.02575   0.01854  -0.0247   0.1377   1.0000
  11.250   1.3408   0.02688   0.01959  -0.0228   0.1310   1.0000
  11.500   1.3497   0.02780   0.02070  -0.0210   0.1242   1.0000
  11.750   1.3572   0.02912   0.02194  -0.0194   0.1180   1.0000
  12.000   1.3648   0.03024   0.02328  -0.0178   0.1118   1.0000
  12.250   1.3705   0.03171   0.02471  -0.0164   0.1061   1.0000
  12.500   1.3770   0.03317   0.02635  -0.0151   0.1006   1.0000
  12.750   1.3815   0.03478   0.02800  -0.0140   0.0954   1.0000
  13.000   1.3861   0.03662   0.02992  -0.0129   0.0905   1.0000
  13.250   1.3898   0.03845   0.03187  -0.0120   0.0857   1.0000
  13.500   1.3926   0.04058   0.03394  -0.0112   0.0812   1.0000
  13.750   1.3941   0.04277   0.03636  -0.0106   0.0772   1.0000
  14.000   1.3953   0.04507   0.03874  -0.0103   0.0734   1.0000
  14.250   1.3963   0.04759   0.04126  -0.0098   0.0698   1.0000
  14.500   1.3953   0.05033   0.04422  -0.0098   0.0665   1.0000
  14.750   1.3939   0.05314   0.04712  -0.0100   0.0634   1.0000
  15.000   1.3940   0.05594   0.04987  -0.0098   0.0601   1.0000
  15.250   1.3898   0.05938   0.05356  -0.0104   0.0579   1.0000
  15.500   1.3862   0.06283   0.05715  -0.0111   0.0553   1.0000
  15.750   1.3836   0.06624   0.06061  -0.0120   0.0530   1.0000
  16.000   1.3823   0.06958   0.06396  -0.0124   0.0506   1.0000
  16.250   1.3746   0.07405   0.06867  -0.0139   0.0489   1.0000
  16.500   1.3682   0.07845   0.07324  -0.0156   0.0470   1.0000
  16.750   1.3642   0.08254   0.07741  -0.0172   0.0453   1.0000
  17.000   1.3659   0.08553   0.08032  -0.0175   0.0429   1.0000
  17.250   1.3541   0.09122   0.08627  -0.0202   0.0420   1.0000
  17.500   1.3418   0.09719   0.09248  -0.0232   0.0408   1.0000
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