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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 100,000
Max Cl/Cd: 29.61 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh82-il-100000.txt
Download as CSV file: xf-mh82-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3548   0.11508   0.11109   0.0079   1.0000   0.0868
  -9.250  -0.3645   0.11280   0.10891   0.0019   1.0000   0.0896
  -9.000  -0.3823   0.11052   0.10678  -0.0063   1.0000   0.0904
  -8.750  -0.3418   0.10411   0.10040  -0.0004   1.0000   0.0929
  -8.500  -0.3262   0.10074   0.09711  -0.0014   1.0000   0.0956
  -8.250  -0.3171   0.09730   0.09378  -0.0048   1.0000   0.0995
  -8.000  -0.3336   0.09413   0.09078  -0.0191   0.9593   0.1036
  -7.750  -0.3051   0.08862   0.08518  -0.0188   0.9083   0.1060
  -7.500  -0.2919   0.08620   0.08264  -0.0158   0.8700   0.1089
  -7.250  -0.2906   0.08382   0.08018  -0.0156   0.8416   0.1122
  -7.000  -0.3073   0.08097   0.07730  -0.0209   0.8205   0.1170
  -6.750  -0.3184   0.07636   0.07257  -0.0272   0.8041   0.1200
  -6.500  -0.3006   0.07392   0.07013  -0.0225   0.7858   0.1225
  -6.250  -0.2912   0.07130   0.06744  -0.0222   0.7693   0.1266
  -6.000  -0.2977   0.06676   0.06265  -0.0299   0.7571   0.1358
  -5.750  -0.2810   0.06405   0.05997  -0.0272   0.7419   0.1387
  -5.500  -0.2688   0.06138   0.05717  -0.0273   0.7290   0.1453
  -5.250  -0.2595   0.05773   0.05334  -0.0293   0.7166   0.1545
  -5.000  -0.2470   0.05496   0.05030  -0.0312   0.7039   0.1690
  -4.750  -0.2228   0.03863   0.03212  -0.0358   0.7017   0.0660
  -4.500  -0.2016   0.03570   0.02890  -0.0351   0.6894   0.0643
  -4.250  -0.1798   0.03293   0.02560  -0.0339   0.6792   0.0630
  -4.000  -0.1547   0.03021   0.02234  -0.0331   0.6663   0.0610
  -3.750  -0.1284   0.02790   0.01943  -0.0320   0.6546   0.0594
  -3.500  -0.1025   0.02627   0.01741  -0.0307   0.6445   0.0600
  -3.250  -0.0748   0.02492   0.01589  -0.0301   0.6315   0.0618
  -3.000  -0.0472   0.02394   0.01465  -0.0292   0.6200   0.0663
  -2.750  -0.0215   0.02284   0.01351  -0.0283   0.6101   0.0733
  -2.500   0.0055   0.02180   0.01250  -0.0276   0.5980   0.0821
  -2.250   0.0313   0.02099   0.01168  -0.0265   0.5883   0.1033
  -2.000   0.0542   0.01943   0.01072  -0.0254   0.5782   0.1937
  -1.750   0.0745   0.01798   0.01035  -0.0241   0.5688   0.4037
  -1.500   0.0993   0.01656   0.01057  -0.0202   0.5595   0.8642
  -1.250   0.2149   0.01664   0.00998  -0.0343   0.5420   1.0000
  -1.000   0.2376   0.01681   0.00993  -0.0337   0.5324   1.0000
  -0.750   0.2601   0.01694   0.00977  -0.0327   0.5245   1.0000
  -0.500   0.2835   0.01720   0.00985  -0.0321   0.5153   1.0000
  -0.250   0.3065   0.01736   0.00975  -0.0311   0.5077   1.0000
   0.000   0.3302   0.01767   0.00991  -0.0305   0.4991   1.0000
   0.250   0.3538   0.01789   0.00993  -0.0297   0.4916   1.0000
   0.500   0.3777   0.01824   0.01012  -0.0290   0.4847   1.0000
   0.750   0.4018   0.01856   0.01032  -0.0284   0.4768   1.0000
   1.000   0.4258   0.01881   0.01030  -0.0274   0.4714   1.0000
   1.250   0.4500   0.01929   0.01080  -0.0271   0.4628   1.0000
   1.500   0.4745   0.01957   0.01089  -0.0263   0.4570   1.0000
   1.750   0.4987   0.02008   0.01133  -0.0259   0.4509   1.0000
   2.000   0.5230   0.02056   0.01175  -0.0254   0.4442   1.0000
   2.250   0.5480   0.02085   0.01185  -0.0246   0.4392   1.0000
   2.500   0.5719   0.02150   0.01253  -0.0243   0.4327   1.0000
   2.750   0.5965   0.02199   0.01296  -0.0239   0.4267   1.0000
   3.000   0.6220   0.02235   0.01317  -0.0232   0.4226   1.0000
   3.250   0.6457   0.02317   0.01404  -0.0230   0.4169   1.0000
   3.500   0.6699   0.02379   0.01467  -0.0227   0.4111   1.0000
   3.750   0.6957   0.02413   0.01488  -0.0222   0.4068   1.0000
   4.000   0.7196   0.02493   0.01569  -0.0219   0.4021   1.0000
   4.250   0.7421   0.02595   0.01682  -0.0218   0.3965   1.0000
   4.500   0.7672   0.02646   0.01728  -0.0214   0.3922   1.0000
   4.750   0.7939   0.02681   0.01748  -0.0209   0.3888   1.0000
   5.000   0.8127   0.02835   0.01926  -0.0210   0.3827   1.0000
   5.250   0.8354   0.02927   0.02023  -0.0207   0.3781   1.0000
   5.500   0.8611   0.02976   0.02065  -0.0203   0.3747   1.0000
   5.750   0.8880   0.03021   0.02097  -0.0199   0.3718   1.0000
   6.000   0.8981   0.03281   0.02399  -0.0201   0.3650   1.0000
   6.250   0.9204   0.03369   0.02489  -0.0198   0.3609   1.0000
   6.500   0.9475   0.03400   0.02513  -0.0194   0.3580   1.0000
   6.750   0.9697   0.03510   0.02624  -0.0191   0.3548   1.0000
   7.000   0.9607   0.03986   0.03147  -0.0194   0.3475   1.0000
   7.250   0.9833   0.04057   0.03219  -0.0189   0.3439   1.0000
   7.500   1.0171   0.04007   0.03158  -0.0183   0.3416   1.0000
   7.750   0.6764   0.08864   0.08090  -0.0387   0.3429   1.0000
   8.000   0.6970   0.09064   0.08290  -0.0384   0.3412   1.0000
   8.250   0.7144   0.09326   0.08555  -0.0383   0.3403   1.0000
   8.500   0.7299   0.09650   0.08879  -0.0385   0.3397   1.0000
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