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MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 43 8.5% (mh43-il)
Reynolds number: 50,000
Max Cl/Cd: 35.49 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh43-il-50000-n5.txt
Download as CSV file: xf-mh43-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 43  8.5%                                     
  
 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  -0.5187   0.09540   0.08883  -0.0068   1.0000   0.0359
  -8.500  -0.5201   0.09045   0.08397  -0.0101   1.0000   0.0348
  -8.250  -0.5249   0.08457   0.07819  -0.0149   1.0000   0.0334
  -7.750  -0.5309   0.07231   0.06589  -0.0258   1.0000   0.0314
  -7.500  -0.5297   0.06769   0.06122  -0.0281   1.0000   0.0311
  -7.250  -0.5275   0.06297   0.05640  -0.0302   1.0000   0.0308
  -7.000  -0.5231   0.05829   0.05155  -0.0320   1.0000   0.0306
  -6.750  -0.5162   0.05368   0.04669  -0.0333   1.0000   0.0304
  -6.500  -0.5066   0.04915   0.04180  -0.0342   1.0000   0.0303
  -6.250  -0.4940   0.04492   0.03716  -0.0346   1.0000   0.0303
  -6.000  -0.4786   0.04094   0.03267  -0.0345   1.0000   0.0306
  -5.750  -0.4605   0.03735   0.02852  -0.0341   1.0000   0.0311
  -5.500  -0.4411   0.03409   0.02480  -0.0334   1.0000   0.0322
  -5.250  -0.4220   0.03182   0.02239  -0.0330   1.0000   0.0362
  -5.000  -0.4002   0.02967   0.01985  -0.0320   1.0000   0.0410
  -4.750  -0.3774   0.02739   0.01716  -0.0307   1.0000   0.0445
  -4.500  -0.3572   0.02556   0.01519  -0.0295   1.0000   0.0510
  -4.250  -0.3372   0.02411   0.01365  -0.0282   1.0000   0.0651
  -4.000  -0.3173   0.02256   0.01197  -0.0265   1.0000   0.0820
  -3.750  -0.2976   0.02118   0.01078  -0.0255   1.0000   0.1208
  -3.500  -0.2795   0.01991   0.00984  -0.0243   1.0000   0.1889
  -3.250  -0.2632   0.01890   0.00926  -0.0230   1.0000   0.2819
  -3.000  -0.2479   0.01803   0.00886  -0.0214   1.0000   0.3862
  -2.750  -0.2342   0.01727   0.00863  -0.0189   1.0000   0.5087
  -2.500  -0.2121   0.01663   0.00854  -0.0170   0.9925   0.6677
  -2.250  -0.1712   0.01631   0.00836  -0.0176   0.9842   0.8436
  -2.000  -0.0893   0.01614   0.00774  -0.0274   0.9844   0.9927
  -1.750  -0.0455   0.01623   0.00740  -0.0314   0.9716   1.0000
  -1.500  -0.0035   0.01632   0.00715  -0.0350   0.9586   1.0000
  -1.250   0.0376   0.01642   0.00691  -0.0382   0.9459   1.0000
  -1.000   0.0764   0.01654   0.00679  -0.0408   0.9329   1.0000
  -0.750   0.1131   0.01667   0.00671  -0.0429   0.9197   1.0000
  -0.500   0.1477   0.01682   0.00665  -0.0445   0.9064   1.0000
  -0.250   0.1800   0.01698   0.00667  -0.0456   0.8930   1.0000
   0.000   0.2103   0.01716   0.00673  -0.0462   0.8795   1.0000
   0.250   0.2388   0.01736   0.00683  -0.0463   0.8659   1.0000
   0.500   0.2660   0.01757   0.00696  -0.0462   0.8524   1.0000
   0.750   0.2921   0.01779   0.00711  -0.0458   0.8388   1.0000
   1.000   0.3174   0.01802   0.00728  -0.0452   0.8253   1.0000
   1.250   0.3423   0.01825   0.00748  -0.0445   0.8118   1.0000
   1.500   0.3667   0.01849   0.00770  -0.0437   0.7981   1.0000
   1.750   0.3910   0.01872   0.00795  -0.0428   0.7843   1.0000
   2.000   0.4151   0.01895   0.00819  -0.0418   0.7703   1.0000
   2.250   0.4391   0.01918   0.00843  -0.0408   0.7561   1.0000
   2.500   0.4631   0.01940   0.00868  -0.0397   0.7417   1.0000
   2.750   0.4875   0.01960   0.00899  -0.0387   0.7270   1.0000
   3.000   0.5119   0.01979   0.00924  -0.0376   0.7120   1.0000
   3.250   0.5359   0.01999   0.00953  -0.0365   0.6960   1.0000
   3.500   0.5596   0.02022   0.00985  -0.0354   0.6785   1.0000
   3.750   0.5836   0.02039   0.01012  -0.0341   0.6610   1.0000
   4.000   0.6079   0.02050   0.01040  -0.0328   0.6435   1.0000
   4.250   0.6312   0.02071   0.01075  -0.0316   0.6222   1.0000
   4.500   0.6550   0.02081   0.01096  -0.0301   0.6011   1.0000
   4.750   0.6784   0.02095   0.01123  -0.0287   0.5771   1.0000
   5.000   0.7014   0.02109   0.01150  -0.0272   0.5503   1.0000
   5.250   0.7242   0.02125   0.01186  -0.0257   0.5204   1.0000
   5.500   0.7463   0.02148   0.01221  -0.0241   0.4853   1.0000
   5.750   0.7677   0.02177   0.01256  -0.0225   0.4456   1.0000
   6.000   0.7882   0.02221   0.01296  -0.0209   0.4005   1.0000
   6.250   0.8072   0.02287   0.01355  -0.0193   0.3488   1.0000
   6.500   0.8245   0.02383   0.01434  -0.0178   0.2942   1.0000
   6.750   0.8402   0.02510   0.01540  -0.0164   0.2398   1.0000
   7.000   0.8549   0.02662   0.01673  -0.0152   0.1905   1.0000
   7.250   0.8686   0.02836   0.01828  -0.0139   0.1503   1.0000
   7.500   0.8818   0.03024   0.02001  -0.0126   0.1197   1.0000
   7.750   0.8955   0.03218   0.02192  -0.0113   0.0959   1.0000
   8.000   0.9086   0.03420   0.02401  -0.0100   0.0789   1.0000
   8.250   0.9248   0.03637   0.02630  -0.0085   0.0678   1.0000
   8.500   0.9397   0.03841   0.02852  -0.0074   0.0567   1.0000
   8.750   0.9572   0.04097   0.03136  -0.0061   0.0494   1.0000
   9.000   0.9741   0.04377   0.03438  -0.0049   0.0449   1.0000
   9.250   0.9876   0.04716   0.03802  -0.0037   0.0411   1.0000
   9.500   0.9943   0.05022   0.04158  -0.0025   0.0368   1.0000
   9.750   0.9980   0.05302   0.04461  -0.0014   0.0336   1.0000
  10.000   0.9997   0.05650   0.04829  -0.0003   0.0323   1.0000
  10.500   0.9850   0.06443   0.05669   0.0016   0.0312   1.0000
  10.750   0.9724   0.06853   0.06105   0.0015   0.0311   1.0000
  11.000   0.9557   0.07335   0.06613   0.0002   0.0310   1.0000
  11.250   0.9409   0.07845   0.07140  -0.0019   0.0311   1.0000
  11.500   0.9251   0.08417   0.07728  -0.0050   0.0312   1.0000
  11.750   0.9090   0.09055   0.08377  -0.0088   0.0314   1.0000
  12.000   0.8751   0.10217   0.09570  -0.0181   0.0334   1.0000
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