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

MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 50,000
Max Cl/Cd: 35.61 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh70-il-50000-n5.txt
Download as CSV file: xf-mh70-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3766   0.09653   0.08977  -0.0293   1.0000   0.0469
  -8.750  -0.3756   0.09257   0.08589  -0.0312   1.0000   0.0464
  -8.500  -0.3753   0.08858   0.08199  -0.0332   1.0000   0.0452
  -8.000  -0.4024   0.07512   0.06874  -0.0449   1.0000   0.0407
  -7.750  -0.4075   0.07085   0.06451  -0.0469   1.0000   0.0406
  -7.500  -0.4119   0.06720   0.06088  -0.0478   1.0000   0.0403
  -7.250  -0.4190   0.06375   0.05742  -0.0478   1.0000   0.0401
  -7.000  -0.4278   0.06063   0.05426  -0.0469   1.0000   0.0400
  -6.750  -0.4360   0.05786   0.05142  -0.0453   1.0000   0.0398
  -6.500  -0.4429   0.05506   0.04847  -0.0435   1.0000   0.0396
  -6.250  -0.4473   0.05195   0.04513  -0.0420   1.0000   0.0396
  -6.000  -0.4366   0.04808   0.04088  -0.0429   0.9956   0.0395
  -5.750  -0.4093   0.04346   0.03565  -0.0463   0.9857   0.0396
  -5.500  -0.3803   0.03951   0.03101  -0.0487   0.9764   0.0401
  -5.250  -0.3484   0.03631   0.02723  -0.0508   0.9683   0.0412
  -5.000  -0.3163   0.03426   0.02500  -0.0527   0.9599   0.0443
  -4.750  -0.2830   0.03211   0.02233  -0.0541   0.9518   0.0479
  -4.500  -0.2477   0.03005   0.01998  -0.0556   0.9446   0.0511
  -4.250  -0.2143   0.02862   0.01829  -0.0567   0.9365   0.0580
  -4.000  -0.1784   0.02717   0.01676  -0.0582   0.9294   0.0664
  -3.750  -0.1459   0.02595   0.01541  -0.0591   0.9210   0.0813
  -3.500  -0.1101   0.02466   0.01415  -0.0606   0.9136   0.1100
  -3.250  -0.0808   0.02333   0.01325  -0.0614   0.9044   0.1781
  -3.000  -0.0487   0.02220   0.01276  -0.0626   0.8969   0.3188
  -2.750  -0.0259   0.02160   0.01260  -0.0617   0.8863   0.4394
  -2.500  -0.0003   0.02106   0.01246  -0.0606   0.8777   0.5551
  -2.250   0.0229   0.02065   0.01241  -0.0584   0.8683   0.6665
  -2.000   0.0530   0.02040   0.01235  -0.0570   0.8598   0.7896
  -1.750   0.1148   0.02020   0.01198  -0.0618   0.8535   0.9149
  -1.500   0.1965   0.01989   0.01121  -0.0716   0.8489   0.9949
  -1.250   0.2188   0.02002   0.01107  -0.0711   0.8364   1.0000
  -1.000   0.2392   0.02019   0.01099  -0.0700   0.8243   1.0000
  -0.750   0.2623   0.02033   0.01089  -0.0691   0.8135   1.0000
  -0.500   0.2869   0.02046   0.01080  -0.0684   0.8029   1.0000
  -0.250   0.3079   0.02068   0.01084  -0.0672   0.7906   1.0000
   0.000   0.3310   0.02087   0.01085  -0.0663   0.7792   1.0000
   0.250   0.3579   0.02095   0.01075  -0.0657   0.7698   1.0000
   0.500   0.3792   0.02120   0.01087  -0.0644   0.7570   1.0000
   0.750   0.4019   0.02141   0.01096  -0.0634   0.7449   1.0000
   1.000   0.4266   0.02156   0.01099  -0.0625   0.7338   1.0000
   1.250   0.4521   0.02166   0.01098  -0.0616   0.7229   1.0000
   1.500   0.4746   0.02190   0.01114  -0.0605   0.7099   1.0000
   1.750   0.4980   0.02210   0.01127  -0.0595   0.6973   1.0000
   2.000   0.5226   0.02224   0.01134  -0.0585   0.6853   1.0000
   2.250   0.5488   0.02229   0.01131  -0.0576   0.6741   1.0000
   2.500   0.5723   0.02248   0.01145  -0.0566   0.6607   1.0000
   2.750   0.5957   0.02268   0.01162  -0.0555   0.6469   1.0000
   3.000   0.6195   0.02286   0.01178  -0.0545   0.6331   1.0000
   3.250   0.6436   0.02302   0.01193  -0.0535   0.6192   1.0000
   3.500   0.6678   0.02318   0.01206  -0.0525   0.6052   1.0000
   3.750   0.6921   0.02333   0.01219  -0.0515   0.5909   1.0000
   4.000   0.7163   0.02349   0.01233  -0.0505   0.5762   1.0000
   4.250   0.7405   0.02367   0.01253  -0.0495   0.5612   1.0000
   4.500   0.7643   0.02387   0.01272  -0.0485   0.5456   1.0000
   4.750   0.7880   0.02410   0.01295  -0.0475   0.5298   1.0000
   5.000   0.8115   0.02436   0.01323  -0.0465   0.5136   1.0000
   5.250   0.8348   0.02465   0.01352  -0.0455   0.4971   1.0000
   5.500   0.8578   0.02497   0.01384  -0.0444   0.4804   1.0000
   5.750   0.8806   0.02533   0.01420  -0.0434   0.4637   1.0000
   6.000   0.9031   0.02573   0.01463  -0.0424   0.4469   1.0000
   6.250   0.9253   0.02617   0.01507  -0.0414   0.4303   1.0000
   6.500   0.9471   0.02666   0.01556  -0.0403   0.4138   1.0000
   6.750   0.9686   0.02720   0.01612  -0.0393   0.3976   1.0000
   7.000   0.9895   0.02779   0.01672  -0.0383   0.3816   1.0000
   7.250   1.0100   0.02844   0.01739  -0.0372   0.3660   1.0000
   7.500   1.0299   0.02913   0.01813  -0.0361   0.3506   1.0000
   7.750   1.0492   0.02990   0.01895  -0.0351   0.3358   1.0000
   8.000   1.0678   0.03072   0.01982  -0.0339   0.3213   1.0000
   8.250   1.0857   0.03159   0.02078  -0.0328   0.3074   1.0000
   8.500   1.1032   0.03254   0.02183  -0.0316   0.2941   1.0000
   8.750   1.1200   0.03351   0.02289  -0.0305   0.2814   1.0000
   9.000   1.1370   0.03452   0.02396  -0.0293   0.2696   1.0000
   9.250   1.1544   0.03549   0.02497  -0.0282   0.2584   1.0000
   9.500   1.1687   0.03662   0.02623  -0.0269   0.2470   1.0000
   9.750   1.1816   0.03792   0.02769  -0.0255   0.2365   1.0000
  10.000   1.1956   0.03911   0.02895  -0.0242   0.2265   1.0000
  10.250   1.2087   0.04031   0.03024  -0.0229   0.2170   1.0000
  10.500   1.2164   0.04191   0.03206  -0.0212   0.2080   1.0000
  10.750   1.2284   0.04311   0.03327  -0.0198   0.1996   1.0000
  11.000   1.2309   0.04493   0.03533  -0.0179   0.1916   1.0000
  11.250   1.2398   0.04645   0.03691  -0.0165   0.1841   1.0000
  11.500   1.2402   0.04851   0.03919  -0.0150   0.1769   1.0000
  11.750   1.2469   0.05026   0.04101  -0.0138   0.1701   1.0000
  12.000   1.2431   0.05291   0.04393  -0.0127   0.1639   1.0000
  12.250   1.2520   0.05451   0.04553  -0.0118   0.1574   1.0000
  12.500   1.2392   0.05823   0.04957  -0.0112   0.1524   1.0000
  12.750   1.2417   0.06055   0.05198  -0.0107   0.1467   1.0000
  13.000   1.2356   0.06398   0.05558  -0.0106   0.1421   1.0000
  13.250   1.2157   0.06923   0.06111  -0.0116   0.1385   1.0000
  13.500   1.2121   0.07255   0.06454  -0.0119   0.1337   1.0000
  13.750   1.2064   0.07641   0.06849  -0.0127   0.1297   1.0000
  14.000   1.1657   0.08585   0.07821  -0.0168   0.1283   1.0000
  14.250   1.0960   0.10219   0.09473  -0.0257   0.1282   1.0000
<< Back to MH 70 11.08% (mh70-il)

Polar data table (+)

Polar graphs


<< Back to MH 70 11.08% (mh70-il)