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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 100,000
Max Cl/Cd: 46.58 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh83-il-100000-n5.txt
Download as CSV file: xf-mh83-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2235   0.10190   0.09722  -0.0142   0.7647   0.0611
  -8.250  -0.2252   0.09903   0.09433  -0.0174   0.7509   0.0628
  -7.750  -0.2249   0.09261   0.08788  -0.0231   0.7248   0.0634
  -7.250  -0.2165   0.08028   0.07544  -0.0262   0.7046   0.0358
  -7.000  -0.2085   0.07779   0.07292  -0.0267   0.6920   0.0352
  -6.750  -0.2036   0.07468   0.06979  -0.0284   0.6814   0.0343
  -6.250  -0.1969   0.06116   0.05614  -0.0431   0.6653   0.0308
  -6.000  -0.1833   0.05621   0.05108  -0.0481   0.6549   0.0304
  -5.750  -0.1688   0.04949   0.04410  -0.0543   0.6470   0.0297
  -5.500  -0.1515   0.04211   0.03625  -0.0606   0.6383   0.0291
  -5.250  -0.1304   0.03630   0.02975  -0.0644   0.6302   0.0288
  -5.000  -0.1056   0.03254   0.02539  -0.0663   0.6194   0.0293
  -4.750  -0.0794   0.02960   0.02177  -0.0673   0.6097   0.0304
  -4.500  -0.0524   0.02749   0.01915  -0.0677   0.5992   0.0315
  -4.250  -0.0254   0.02616   0.01758  -0.0678   0.5884   0.0324
  -4.000   0.0019   0.02477   0.01584  -0.0677   0.5788   0.0331
  -3.750   0.0300   0.02352   0.01434  -0.0676   0.5679   0.0340
  -3.500   0.0578   0.02245   0.01296  -0.0673   0.5587   0.0352
  -3.250   0.0857   0.02154   0.01188  -0.0671   0.5482   0.0365
  -3.000   0.1133   0.02091   0.01116  -0.0669   0.5388   0.0388
  -2.750   0.1412   0.02031   0.01042  -0.0667   0.5292   0.0423
  -2.500   0.1692   0.01979   0.00980  -0.0665   0.5199   0.0463
  -2.250   0.1972   0.01926   0.00918  -0.0663   0.5111   0.0509
  -2.000   0.2255   0.01879   0.00865  -0.0662   0.5022   0.0608
  -1.750   0.2537   0.01829   0.00818  -0.0661   0.4939   0.0852
  -1.500   0.2817   0.01785   0.00790  -0.0661   0.4854   0.1330
  -1.250   0.3092   0.01751   0.00779  -0.0661   0.4772   0.2034
  -1.000   0.3370   0.01728   0.00771  -0.0660   0.4693   0.2713
  -0.750   0.3645   0.01710   0.00762  -0.0658   0.4617   0.3333
  -0.500   0.3918   0.01694   0.00754  -0.0655   0.4550   0.4006
  -0.250   0.4191   0.01676   0.00756  -0.0652   0.4471   0.4828
   0.000   0.4447   0.01653   0.00752  -0.0644   0.4410   0.5885
   0.250   0.4673   0.01620   0.00758  -0.0626   0.4339   0.7283
   0.500   0.5001   0.01586   0.00740  -0.0627   0.4270   1.0000
   0.750   0.5286   0.01610   0.00739  -0.0626   0.4214   1.0000
   1.000   0.5570   0.01635   0.00748  -0.0627   0.4148   1.0000
   1.250   0.5852   0.01659   0.00750  -0.0626   0.4092   1.0000
   1.500   0.6132   0.01686   0.00759  -0.0626   0.4036   1.0000
   1.750   0.6413   0.01714   0.00775  -0.0626   0.3975   1.0000
   2.000   0.6691   0.01741   0.00785  -0.0625   0.3925   1.0000
   2.250   0.6969   0.01773   0.00801  -0.0624   0.3880   1.0000
   2.500   0.7246   0.01806   0.00828  -0.0624   0.3826   1.0000
   2.750   0.7521   0.01836   0.00846  -0.0623   0.3778   1.0000
   3.000   0.7796   0.01867   0.00860  -0.0621   0.3739   1.0000
   3.250   0.8068   0.01905   0.00896  -0.0621   0.3688   1.0000
   3.500   0.8340   0.01941   0.00927  -0.0620   0.3641   1.0000
   3.750   0.8612   0.01976   0.00952  -0.0619   0.3604   1.0000
   4.000   0.8883   0.02013   0.00975  -0.0618   0.3572   1.0000
   4.250   0.9149   0.02058   0.01024  -0.0617   0.3527   1.0000
   4.500   0.9414   0.02100   0.01065  -0.0616   0.3484   1.0000
   4.750   0.9680   0.02138   0.01098  -0.0615   0.3446   1.0000
   5.000   0.9948   0.02176   0.01126  -0.0614   0.3416   1.0000
   5.250   1.0207   0.02228   0.01181  -0.0613   0.3381   1.0000
   5.500   1.0463   0.02281   0.01239  -0.0612   0.3343   1.0000
   5.750   1.0720   0.02329   0.01288  -0.0610   0.3307   1.0000
   6.000   1.0981   0.02371   0.01325  -0.0608   0.3275   1.0000
   6.250   1.1244   0.02414   0.01358  -0.0607   0.3249   1.0000
   6.500   1.1482   0.02481   0.01441  -0.0605   0.3212   1.0000
   6.750   1.1724   0.02545   0.01514  -0.0603   0.3178   1.0000
   7.000   1.1969   0.02601   0.01573  -0.0601   0.3146   1.0000
   7.250   1.2221   0.02649   0.01621  -0.0599   0.3117   1.0000
   7.500   1.2479   0.02695   0.01659  -0.0597   0.3093   1.0000
   7.750   1.2695   0.02777   0.01758  -0.0594   0.3059   1.0000
   8.000   1.2910   0.02860   0.01856  -0.0590   0.3027   1.0000
   8.250   1.3132   0.02931   0.01935  -0.0587   0.2996   1.0000
   8.500   1.3367   0.02989   0.01996  -0.0584   0.2968   1.0000
   8.750   1.3615   0.03038   0.02042  -0.0581   0.2944   1.0000
   9.000   1.3825   0.03120   0.02134  -0.0577   0.2917   1.0000
   9.250   1.3982   0.03239   0.02276  -0.0571   0.2884   1.0000
   9.500   1.4155   0.03341   0.02392  -0.0565   0.2853   1.0000
   9.750   1.4350   0.03420   0.02481  -0.0559   0.2825   1.0000
  10.000   1.4573   0.03478   0.02540  -0.0555   0.2800   1.0000
  10.250   1.4824   0.03525   0.02584  -0.0553   0.2779   1.0000
  10.500   1.4876   0.03702   0.02790  -0.0540   0.2747   1.0000
  10.750   1.4916   0.03877   0.02989  -0.0527   0.2715   1.0000
  11.000   1.4987   0.04020   0.03147  -0.0515   0.2686   1.0000
  11.250   1.5115   0.04115   0.03248  -0.0505   0.2660   1.0000
  11.500   1.5330   0.04166   0.03301  -0.0500   0.2639   1.0000
  11.750   1.5443   0.04282   0.03424  -0.0490   0.2617   1.0000
  12.000   1.4837   0.04912   0.04093  -0.0469   0.2580   1.0000
  12.250   1.3832   0.06255   0.05468  -0.0504   0.2516   1.0000
  12.500   1.4090   0.06225   0.05441  -0.0495   0.2498   1.0000
  12.750   1.4516   0.06000   0.05217  -0.0479   0.2486   1.0000
  16.250   1.1252   0.17061   0.16392  -0.0978   0.1616   1.0000
  16.500   1.1298   0.17397   0.16734  -0.0995   0.1577   1.0000
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