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MH 81 13% (mh81-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 81 13% (mh81-il)
Reynolds number: 50,000
Max Cl/Cd: 22.96 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh81-il-50000-n5.txt
Download as CSV file: xf-mh81-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3998   0.09719   0.09146  -0.0009   1.0000   0.0494
  -8.500  -0.3985   0.09250   0.08688  -0.0040   1.0000   0.0479
  -8.250  -0.4114   0.08467   0.07913  -0.0121   1.0000   0.0449
  -8.000  -0.4087   0.08034   0.07490  -0.0154   1.0000   0.0444
  -7.750  -0.4082   0.07603   0.07068  -0.0185   1.0000   0.0438
  -7.500  -0.4079   0.07120   0.06588  -0.0220   1.0000   0.0431
  -7.250  -0.4079   0.06613   0.06079  -0.0256   1.0000   0.0424
  -7.000  -0.4001   0.06051   0.05496  -0.0304   0.9307   0.0416
  -6.750  -0.3908   0.05522   0.04926  -0.0335   0.8886   0.0409
  -6.500  -0.3838   0.05090   0.04446  -0.0340   0.8583   0.0405
  -6.250  -0.3751   0.04728   0.04034  -0.0332   0.8335   0.0404
  -6.000  -0.3633   0.04428   0.03685  -0.0320   0.8120   0.0406
  -5.750  -0.3484   0.04172   0.03385  -0.0307   0.7914   0.0414
  -5.500  -0.3316   0.03930   0.03093  -0.0294   0.7727   0.0429
  -5.250  -0.3127   0.03685   0.02784  -0.0279   0.7555   0.0446
  -5.000  -0.2918   0.03503   0.02571  -0.0267   0.7386   0.0463
  -4.750  -0.2694   0.03339   0.02377  -0.0255   0.7224   0.0481
  -4.500  -0.2455   0.03173   0.02171  -0.0242   0.7073   0.0500
  -4.250  -0.2212   0.03031   0.02000  -0.0229   0.6926   0.0535
  -4.000  -0.1959   0.02918   0.01867  -0.0220   0.6773   0.0586
  -3.750  -0.1704   0.02804   0.01740  -0.0211   0.6627   0.0641
  -3.500  -0.1446   0.02707   0.01629  -0.0201   0.6489   0.0729
  -3.250  -0.1189   0.02615   0.01528  -0.0192   0.6361   0.0866
  -3.000  -0.0931   0.02519   0.01431  -0.0184   0.6234   0.1117
  -2.750  -0.0680   0.02407   0.01346  -0.0178   0.6104   0.1697
  -2.500  -0.0466   0.02296   0.01288  -0.0169   0.5990   0.2745
  -2.250  -0.0297   0.02173   0.01253  -0.0147   0.5883   0.4475
  -2.000   0.0010   0.02070   0.01278  -0.0121   0.5757   0.7580
  -1.750   0.0548   0.02094   0.01268  -0.0142   0.5620   0.9078
  -1.500   0.1229   0.02103   0.01218  -0.0205   0.5474   0.9714
  -1.250   0.1794   0.02093   0.01157  -0.0258   0.5347   1.0000
  -1.000   0.2017   0.02108   0.01149  -0.0253   0.5237   1.0000
  -0.750   0.2232   0.02120   0.01129  -0.0242   0.5154   1.0000
  -0.500   0.2460   0.02143   0.01132  -0.0236   0.5051   1.0000
  -0.250   0.2684   0.02162   0.01123  -0.0227   0.4972   1.0000
   0.000   0.2914   0.02190   0.01135  -0.0221   0.4876   1.0000
   0.250   0.3139   0.02213   0.01131  -0.0211   0.4802   1.0000
   0.500   0.3371   0.02249   0.01155  -0.0205   0.4712   1.0000
   0.750   0.3597   0.02272   0.01153  -0.0194   0.4649   1.0000
   1.000   0.3830   0.02319   0.01192  -0.0190   0.4558   1.0000
   1.250   0.4058   0.02347   0.01200  -0.0181   0.4494   1.0000
   1.500   0.4289   0.02397   0.01241  -0.0176   0.4418   1.0000
   1.750   0.4519   0.02438   0.01270  -0.0168   0.4350   1.0000
   2.000   0.4750   0.02473   0.01286  -0.0159   0.4295   1.0000
   2.250   0.4976   0.02537   0.01352  -0.0155   0.4216   1.0000
   2.500   0.5207   0.02575   0.01375  -0.0146   0.4161   1.0000
   2.750   0.5434   0.02636   0.01430  -0.0141   0.4102   1.0000
   3.000   0.5657   0.02703   0.01496  -0.0136   0.4036   1.0000
   3.250   0.5890   0.02742   0.01522  -0.0127   0.3988   1.0000
   3.500   0.6110   0.02820   0.01601  -0.0123   0.3928   1.0000
   3.750   0.6328   0.02898   0.01679  -0.0118   0.3868   1.0000
   4.000   0.6562   0.02944   0.01716  -0.0110   0.3825   1.0000
   4.250   0.6778   0.03029   0.01803  -0.0106   0.3773   1.0000
   4.500   0.6979   0.03135   0.01917  -0.0103   0.3712   1.0000
   4.750   0.7208   0.03191   0.01967  -0.0096   0.3668   1.0000
   5.000   0.7445   0.03242   0.02009  -0.0089   0.3632   1.0000
   5.250   0.7595   0.03420   0.02209  -0.0089   0.3566   1.0000
   5.500   0.7803   0.03508   0.02300  -0.0084   0.3520   1.0000
   5.750   0.8046   0.03549   0.02333  -0.0076   0.3486   1.0000
   6.000   0.8171   0.03745   0.02548  -0.0075   0.3429   1.0000
   6.250   0.8311   0.03914   0.02729  -0.0072   0.3377   1.0000
   6.500   0.8525   0.03990   0.02807  -0.0066   0.3341   1.0000
   6.750   0.8788   0.04014   0.02822  -0.0059   0.3314   1.0000
   7.000   0.8653   0.04479   0.03324  -0.0063   0.3234   1.0000
   7.250   0.8788   0.04632   0.03482  -0.0059   0.3193   1.0000
   7.500   0.9028   0.04677   0.03528  -0.0051   0.3166   1.0000
   8.000   0.8403   0.05916   0.04793  -0.0075   0.3022   1.0000
   8.250   0.8699   0.05875   0.04755  -0.0061   0.3003   1.0000
   8.750   0.8007   0.07468   0.06355  -0.0126   0.2849   1.0000
   9.250   0.7652   0.08657   0.07550  -0.0173   0.2725   1.0000
   9.500   0.7817   0.08799   0.07697  -0.0169   0.2699   1.0000
   9.750   0.7673   0.09360   0.08261  -0.0191   0.2646   1.0000
  10.000   0.7610   0.09807   0.08712  -0.0208   0.2593   1.0000
  10.250   0.7715   0.10038   0.08947  -0.0210   0.2562   1.0000
  10.500   0.7895   0.10174   0.09087  -0.0205   0.2539   1.0000
  10.750   0.7679   0.10850   0.09768  -0.0237   0.2482   1.0000
  11.000   0.7693   0.11201   0.10123  -0.0248   0.2437   1.0000
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