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MH 81 13% (mh81-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 81 13% (mh81-il)
Reynolds number: 100,000
Max Cl/Cd: 28.85 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh81-il-100000.txt
Download as CSV file: xf-mh81-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 81  13%                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3905   0.10336   0.09950   0.0088   1.0000   0.0988
  -8.500  -0.3951   0.10001   0.09625   0.0044   1.0000   0.1033
  -8.250  -0.4293   0.09651   0.09293  -0.0079   1.0000   0.1050
  -8.000  -0.3871   0.09176   0.08821  -0.0007   1.0000   0.1079
  -7.750  -0.3722   0.08852   0.08505  -0.0016   1.0000   0.1114
  -7.500  -0.3732   0.08464   0.08132  -0.0078   1.0000   0.1167
  -7.250  -0.3809   0.07828   0.07501  -0.0210   0.9431   0.1209
  -7.000  -0.3546   0.07568   0.07234  -0.0181   0.8922   0.1244
  -6.750  -0.3546   0.07308   0.06962  -0.0181   0.8573   0.1290
  -6.500  -0.3718   0.06869   0.06497  -0.0238   0.8344   0.1362
  -6.250  -0.3573   0.06620   0.06247  -0.0204   0.8122   0.1392
  -6.000  -0.3496   0.06351   0.05965  -0.0205   0.7923   0.1459
  -5.750  -0.3465   0.05983   0.05578  -0.0218   0.7761   0.1541
  -5.500  -0.3414   0.05740   0.05299  -0.0230   0.7608   0.1682
  -5.250  -0.3271   0.03857   0.03217  -0.0261   0.7586   0.0611
  -5.000  -0.3078   0.03587   0.02906  -0.0245   0.7437   0.0589
  -4.750  -0.2872   0.03329   0.02602  -0.0232   0.7285   0.0584
  -4.500  -0.2644   0.03099   0.02326  -0.0220   0.7135   0.0583
  -4.250  -0.2402   0.02886   0.02069  -0.0207   0.6989   0.0580
  -4.000  -0.2147   0.02698   0.01840  -0.0195   0.6851   0.0580
  -3.750  -0.1884   0.02539   0.01641  -0.0181   0.6724   0.0590
  -3.500  -0.1619   0.02391   0.01472  -0.0171   0.6590   0.0614
  -3.250  -0.1354   0.02298   0.01374  -0.0163   0.6449   0.0677
  -3.000  -0.1095   0.02189   0.01266  -0.0154   0.6321   0.0753
  -2.750  -0.0848   0.02093   0.01166  -0.0141   0.6214   0.0890
  -2.500  -0.0604   0.01980   0.01077  -0.0130   0.6085   0.1237
  -2.250  -0.0414   0.01785   0.00993  -0.0114   0.5978   0.3089
  -1.750   0.0339   0.01636   0.01037  -0.0091   0.5729   0.9341
  -1.500   0.1534   0.01650   0.00975  -0.0247   0.5533   0.9982
  -1.250   0.1797   0.01654   0.00957  -0.0248   0.5420   1.0000
  -1.000   0.2012   0.01660   0.00930  -0.0238   0.5338   1.0000
  -0.750   0.2247   0.01673   0.00931  -0.0233   0.5226   1.0000
  -0.500   0.2473   0.01688   0.00920  -0.0224   0.5148   1.0000
  -0.250   0.2709   0.01707   0.00927  -0.0219   0.5048   1.0000
   0.000   0.2938   0.01727   0.00923  -0.0210   0.4974   1.0000
   0.250   0.3177   0.01751   0.00938  -0.0204   0.4878   1.0000
   0.500   0.3407   0.01772   0.00934  -0.0194   0.4814   1.0000
   0.750   0.3648   0.01808   0.00969  -0.0190   0.4723   1.0000
   1.000   0.3882   0.01831   0.00971  -0.0181   0.4661   1.0000
   1.250   0.4121   0.01873   0.01011  -0.0176   0.4580   1.0000
   1.500   0.4358   0.01901   0.01024  -0.0168   0.4512   1.0000
   1.750   0.4594   0.01940   0.01051  -0.0161   0.4452   1.0000
   2.000   0.4832   0.01987   0.01099  -0.0156   0.4379   1.0000
   2.250   0.5071   0.02018   0.01115  -0.0148   0.4327   1.0000
   2.500   0.5306   0.02075   0.01171  -0.0143   0.4263   1.0000
   2.750   0.5543   0.02122   0.01215  -0.0137   0.4198   1.0000
   3.000   0.5784   0.02154   0.01231  -0.0129   0.4152   1.0000
   3.250   0.6015   0.02230   0.01314  -0.0125   0.4094   1.0000
   3.500   0.6248   0.02290   0.01376  -0.0120   0.4036   1.0000
   3.750   0.6491   0.02325   0.01399  -0.0112   0.3991   1.0000
   4.000   0.6718   0.02402   0.01478  -0.0107   0.3939   1.0000
   4.250   0.6942   0.02483   0.01569  -0.0103   0.3881   1.0000
   4.500   0.7183   0.02533   0.01613  -0.0097   0.3839   1.0000
   4.750   0.7435   0.02577   0.01641  -0.0090   0.3805   1.0000
   5.000   0.7623   0.02719   0.01812  -0.0089   0.3740   1.0000
   5.250   0.7856   0.02785   0.01879  -0.0084   0.3692   1.0000
   5.500   0.8108   0.02825   0.01910  -0.0078   0.3657   1.0000
   5.750   0.8311   0.02955   0.02052  -0.0076   0.3614   1.0000
   6.000   0.8481   0.03120   0.02238  -0.0074   0.3556   1.0000
   6.250   0.8725   0.03170   0.02286  -0.0069   0.3516   1.0000
   6.500   0.8993   0.03196   0.02301  -0.0063   0.3485   1.0000
   6.750   0.9081   0.03475   0.02615  -0.0064   0.3430   1.0000
   7.000   0.9209   0.03683   0.02841  -0.0062   0.3379   1.0000
   7.250   0.9474   0.03704   0.02858  -0.0056   0.3346   1.0000
   7.500   0.9783   0.03686   0.02826  -0.0050   0.3319   1.0000
   7.750   0.9219   0.04722   0.03935  -0.0065   0.3227   1.0000
   8.000   0.9300   0.04950   0.04169  -0.0063   0.3190   1.0000
   8.250   0.9848   0.04637   0.03844  -0.0047   0.3174   1.0000
   8.500   1.0332   0.04432   0.03623  -0.0037   0.3156   1.0000
   8.750   0.7091   0.09171   0.08407  -0.0243   0.3145   1.0000
   9.000   0.7215   0.09521   0.08762  -0.0248   0.3154   1.0000
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