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MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 42 8.94% (mh42-il)
Reynolds number: 50,000
Max Cl/Cd: 35.49 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh42-il-50000-n5.txt
Download as CSV file: xf-mh42-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 42  8.94%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5097   0.11913   0.11219   0.0005   1.0000   0.0413
 -10.000  -0.5077   0.11468   0.10779  -0.0017   1.0000   0.0394
  -9.500  -0.5119   0.10420   0.09744  -0.0096   1.0000   0.0349
  -9.250  -0.5082   0.10009   0.09338  -0.0108   1.0000   0.0345
  -9.000  -0.5058   0.09591   0.08926  -0.0125   1.0000   0.0340
  -8.750  -0.5047   0.09158   0.08500  -0.0146   1.0000   0.0337
  -8.500  -0.5041   0.08730   0.08079  -0.0170   1.0000   0.0332
  -8.250  -0.5062   0.08245   0.07602  -0.0201   1.0000   0.0329
  -8.000  -0.5095   0.07752   0.07117  -0.0239   1.0000   0.0324
  -7.750  -0.5115   0.07235   0.06601  -0.0275   1.0000   0.0320
  -7.500  -0.5134   0.06711   0.06073  -0.0305   1.0000   0.0316
  -7.250  -0.5132   0.06222   0.05573  -0.0329   1.0000   0.0312
  -7.000  -0.5111   0.05733   0.05067  -0.0347   1.0000   0.0309
  -6.750  -0.5063   0.05258   0.04556  -0.0358   1.0000   0.0308
  -6.500  -0.4982   0.04816   0.04077  -0.0363   1.0000   0.0313
  -6.250  -0.4872   0.04403   0.03617  -0.0363   1.0000   0.0324
  -6.000  -0.4731   0.04031   0.03186  -0.0357   1.0000   0.0340
  -5.750  -0.4562   0.03721   0.02818  -0.0348   1.0000   0.0353
  -5.500  -0.4401   0.03418   0.02495  -0.0340   1.0000   0.0375
  -5.250  -0.4211   0.03171   0.02217  -0.0328   1.0000   0.0393
  -5.000  -0.4011   0.02942   0.01954  -0.0313   1.0000   0.0420
  -4.750  -0.3803   0.02764   0.01734  -0.0298   1.0000   0.0479
  -4.500  -0.3621   0.02599   0.01569  -0.0284   1.0000   0.0560
  -4.250  -0.3428   0.02435   0.01393  -0.0266   1.0000   0.0649
  -4.000  -0.3243   0.02316   0.01269  -0.0251   1.0000   0.0830
  -3.500  -0.2865   0.02057   0.01034  -0.0226   1.0000   0.1683
  -3.250  -0.2700   0.01956   0.00975  -0.0214   1.0000   0.2531
  -3.000  -0.2543   0.01871   0.00934  -0.0199   1.0000   0.3521
  -2.750  -0.2343   0.01787   0.00907  -0.0188   0.9960   0.4840
  -2.500  -0.2046   0.01714   0.00900  -0.0183   0.9843   0.6597
  -2.250  -0.1617   0.01683   0.00892  -0.0192   0.9765   0.8386
  -2.000  -0.0773   0.01671   0.00832  -0.0293   0.9766   0.9833
  -1.750  -0.0279   0.01677   0.00795  -0.0343   0.9657   1.0000
  -1.500   0.0152   0.01685   0.00768  -0.0381   0.9526   1.0000
  -1.250   0.0569   0.01692   0.00744  -0.0413   0.9394   1.0000
  -1.000   0.0954   0.01702   0.00729  -0.0438   0.9256   1.0000
  -0.750   0.1314   0.01712   0.00719  -0.0457   0.9115   1.0000
  -0.500   0.1649   0.01724   0.00712  -0.0470   0.8970   1.0000
  -0.250   0.1960   0.01738   0.00711  -0.0478   0.8824   1.0000
   0.000   0.2252   0.01753   0.00713  -0.0481   0.8677   1.0000
   0.250   0.2528   0.01769   0.00719  -0.0480   0.8532   1.0000
   0.500   0.2793   0.01786   0.00726  -0.0476   0.8387   1.0000
   0.750   0.3049   0.01804   0.00737  -0.0471   0.8245   1.0000
   1.000   0.3299   0.01824   0.00749  -0.0463   0.8102   1.0000
   1.250   0.3545   0.01843   0.00764  -0.0455   0.7960   1.0000
   1.500   0.3788   0.01863   0.00783  -0.0446   0.7818   1.0000
   1.750   0.4029   0.01884   0.00800  -0.0436   0.7676   1.0000
   2.000   0.4269   0.01904   0.00819  -0.0426   0.7533   1.0000
   2.250   0.4509   0.01925   0.00840  -0.0416   0.7390   1.0000
   2.500   0.4752   0.01946   0.00861  -0.0405   0.7244   1.0000
   2.750   0.4996   0.01966   0.00889  -0.0395   0.7097   1.0000
   3.000   0.5240   0.01986   0.00912  -0.0385   0.6948   1.0000
   3.250   0.5476   0.02011   0.00943  -0.0374   0.6783   1.0000
   3.500   0.5714   0.02034   0.00974  -0.0364   0.6614   1.0000
   3.750   0.5954   0.02055   0.01007  -0.0352   0.6444   1.0000
   4.000   0.6196   0.02073   0.01031  -0.0340   0.6273   1.0000
   4.250   0.6431   0.02097   0.01066  -0.0329   0.6080   1.0000
   4.500   0.6667   0.02117   0.01095  -0.0317   0.5882   1.0000
   4.750   0.6901   0.02138   0.01127  -0.0304   0.5669   1.0000
   5.000   0.7136   0.02156   0.01161  -0.0290   0.5448   1.0000
   5.250   0.7362   0.02181   0.01198  -0.0277   0.5195   1.0000
   5.500   0.7587   0.02206   0.01233  -0.0263   0.4926   1.0000
   5.750   0.7807   0.02234   0.01268  -0.0249   0.4634   1.0000
   6.000   0.8019   0.02272   0.01314  -0.0234   0.4306   1.0000
   6.250   0.8224   0.02317   0.01361  -0.0219   0.3954   1.0000
   6.500   0.8417   0.02376   0.01431  -0.0204   0.3567   1.0000
   6.750   0.8597   0.02453   0.01503  -0.0189   0.3157   1.0000
   7.000   0.8763   0.02549   0.01592  -0.0174   0.2743   1.0000
   7.250   0.8915   0.02668   0.01700  -0.0159   0.2338   1.0000
   7.500   0.9056   0.02806   0.01828  -0.0145   0.1965   1.0000
   7.750   0.9182   0.02963   0.01973  -0.0130   0.1644   1.0000
   8.000   0.9303   0.03136   0.02137  -0.0116   0.1375   1.0000
   8.250   0.9420   0.03315   0.02315  -0.0101   0.1138   1.0000
   8.750   0.9650   0.03710   0.02711  -0.0071   0.0831   1.0000
   9.000   0.9751   0.03909   0.02914  -0.0058   0.0714   1.0000
   9.250   0.9911   0.04145   0.03191  -0.0043   0.0631   1.0000
   9.500   1.0044   0.04398   0.03460  -0.0030   0.0565   1.0000
   9.750   1.0121   0.04621   0.03703  -0.0017   0.0501   1.0000
  10.000   1.0218   0.04919   0.04019  -0.0004   0.0461   1.0000
  10.250   1.0278   0.05271   0.04418   0.0011   0.0435   1.0000
  10.500   1.0267   0.05613   0.04794   0.0026   0.0415   1.0000
  10.750   1.0219   0.05932   0.05135   0.0037   0.0395   1.0000
  11.000   1.0167   0.06246   0.05462   0.0041   0.0378   1.0000
  11.250   1.0096   0.06626   0.05846   0.0041   0.0361   1.0000
  11.500   0.9950   0.07085   0.06335   0.0030   0.0358   1.0000
  11.750   0.9789   0.07609   0.06883   0.0010   0.0356   1.0000
  12.000   0.9624   0.08189   0.07484  -0.0018   0.0357   1.0000
  12.250   0.9454   0.08831   0.08141  -0.0053   0.0359   1.0000
  12.500   0.9292   0.09517   0.08839  -0.0093   0.0361   1.0000
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