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MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 80 12.72% (mh80-il)
Reynolds number: 100,000
Max Cl/Cd: 28.32 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh80-il-100000.txt
Download as CSV file: xf-mh80-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 80  12.72%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4500   0.09849   0.09464   0.0140   1.0000   0.1079
  -8.250  -0.4717   0.09444   0.09071   0.0058   1.0000   0.1128
  -8.000  -0.5184   0.09015   0.08640  -0.0055   1.0000   0.1138
  -7.750  -0.4526   0.08609   0.08253   0.0050   1.0000   0.1181
  -7.500  -0.4478   0.08251   0.07903   0.0028   1.0000   0.1224
  -7.250  -0.4996   0.07795   0.07425  -0.0111   1.0000   0.1289
  -7.000  -0.4574   0.07309   0.06976  -0.0071   1.0000   0.1322
  -6.750  -0.4418   0.06971   0.06646  -0.0098   1.0000   0.1395
  -6.500  -0.4223   0.06494   0.06162  -0.0153   0.9232   0.1505
  -6.000  -0.4163   0.05924   0.05553  -0.0141   0.8462   0.1659
  -5.750  -0.4223   0.04043   0.03452  -0.0187   0.8405   0.0651
  -5.500  -0.4069   0.03778   0.03149  -0.0163   0.8177   0.0623
  -5.250  -0.3907   0.03485   0.02814  -0.0142   0.7975   0.0603
  -5.000  -0.3721   0.03136   0.02370  -0.0116   0.7793   0.0557
  -4.750  -0.3492   0.02975   0.02153  -0.0096   0.7600   0.0545
  -4.500  -0.3255   0.02782   0.01924  -0.0081   0.7420   0.0546
  -4.250  -0.3007   0.02581   0.01700  -0.0068   0.7249   0.0554
  -4.000  -0.2755   0.02434   0.01543  -0.0057   0.7081   0.0576
  -3.750  -0.2498   0.02339   0.01427  -0.0045   0.6920   0.0629
  -3.500  -0.2248   0.02214   0.01304  -0.0034   0.6769   0.0689
  -3.250  -0.2003   0.02102   0.01184  -0.0019   0.6629   0.0774
  -3.000  -0.1765   0.02005   0.01094  -0.0006   0.6484   0.0977
  -2.750  -0.1567   0.01816   0.00983   0.0011   0.6349   0.2047
  -2.500  -0.1419   0.01635   0.00938   0.0034   0.6226   0.4630
  -2.250  -0.1098   0.01555   0.00991   0.0065   0.6092   0.8266
  -2.000  -0.0384   0.01660   0.01055   0.0026   0.5908   0.9408
  -1.750   0.0546   0.01686   0.01024  -0.0083   0.5703   0.9810
  -1.500   0.1172   0.01666   0.00962  -0.0150   0.5542   1.0000
  -1.250   0.1384   0.01664   0.00932  -0.0141   0.5444   1.0000
  -1.000   0.1616   0.01668   0.00920  -0.0136   0.5323   1.0000
  -0.750   0.1844   0.01676   0.00908  -0.0130   0.5225   1.0000
  -0.500   0.2076   0.01683   0.00896  -0.0123   0.5127   1.0000
  -0.250   0.2315   0.01699   0.00898  -0.0118   0.5026   1.0000
   0.000   0.2544   0.01711   0.00888  -0.0109   0.4942   1.0000
   0.250   0.2786   0.01733   0.00903  -0.0105   0.4842   1.0000
   0.500   0.3017   0.01751   0.00899  -0.0096   0.4770   1.0000
   0.750   0.3261   0.01780   0.00926  -0.0093   0.4677   1.0000
   1.000   0.3494   0.01800   0.00927  -0.0084   0.4607   1.0000
   1.250   0.3737   0.01835   0.00959  -0.0080   0.4522   1.0000
   1.500   0.3972   0.01860   0.00970  -0.0072   0.4453   1.0000
   1.750   0.4211   0.01900   0.01005  -0.0067   0.4385   1.0000
   2.000   0.4449   0.01936   0.01037  -0.0061   0.4312   1.0000
   2.250   0.4682   0.01965   0.01046  -0.0051   0.4260   1.0000
   2.500   0.4921   0.02019   0.01110  -0.0048   0.4181   1.0000
   2.750   0.5156   0.02053   0.01136  -0.0041   0.4125   1.0000
   3.000   0.5389   0.02103   0.01179  -0.0034   0.4073   1.0000
   3.250   0.5621   0.02163   0.01247  -0.0030   0.4004   1.0000
   3.500   0.5855   0.02196   0.01270  -0.0021   0.3953   1.0000
   3.750   0.6083   0.02260   0.01335  -0.0015   0.3900   1.0000
   4.000   0.6308   0.02333   0.01418  -0.0010   0.3840   1.0000
   4.250   0.6541   0.02375   0.01452  -0.0002   0.3794   1.0000
   4.500   0.6769   0.02436   0.01510   0.0005   0.3750   1.0000
   4.750   0.6977   0.02534   0.01626   0.0009   0.3685   1.0000
   5.000   0.7207   0.02584   0.01673   0.0017   0.3640   1.0000
   5.250   0.7447   0.02630   0.01706   0.0025   0.3606   1.0000
   5.500   0.7624   0.02781   0.01886   0.0028   0.3545   1.0000
   5.750   0.7839   0.02855   0.01966   0.0034   0.3495   1.0000
   6.000   0.8082   0.02887   0.01988   0.0043   0.3458   1.0000
   6.250   0.8262   0.03032   0.02148   0.0047   0.3412   1.0000
   6.500   0.8416   0.03207   0.02348   0.0051   0.3357   1.0000
   6.750   0.8651   0.03254   0.02393   0.0058   0.3317   1.0000
   7.000   0.8916   0.03272   0.02398   0.0066   0.3286   1.0000
   7.250   0.8945   0.03612   0.02783   0.0066   0.3221   1.0000
   7.500   0.9084   0.03796   0.02981   0.0070   0.3177   1.0000
   7.750   0.9361   0.03795   0.02973   0.0078   0.3146   1.0000
   8.000   0.9642   0.03812   0.02980   0.0085   0.3118   1.0000
   8.250   0.7579   0.06778   0.06025  -0.0031   0.2982   1.0000
   8.500   0.9222   0.04970   0.04213   0.0073   0.2992   1.0000
   8.750   0.9795   0.04635   0.03864   0.0092   0.2977   1.0000
   9.000   0.6894   0.08968   0.08218  -0.0121   0.2974   1.0000
   9.250   0.5915   0.10640   0.09899  -0.0230   0.3340   1.0000
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