Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 92 15.49% (mh92-il)
Reynolds number: 500,000
Max Cl/Cd: 73.42 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh92-il-500000-n5.txt
Download as CSV file: xf-mh92-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 92  15.49%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9215   0.11053   0.10735   0.0114   1.0000   0.0064
 -16.500  -0.9513   0.09935   0.09596   0.0044   1.0000   0.0064
 -16.250  -0.9788   0.08930   0.08568  -0.0018   1.0000   0.0064
 -16.000  -0.9946   0.08202   0.07825  -0.0063   1.0000   0.0064
 -15.750  -1.0128   0.07467   0.07071  -0.0106   1.0000   0.0064
 -15.500  -1.0249   0.06875   0.06465  -0.0139   1.0000   0.0065
 -15.250  -1.0362   0.06334   0.05907  -0.0167   1.0000   0.0064
 -15.000  -1.0440   0.05872   0.05431  -0.0188   1.0000   0.0065
 -14.750  -1.0519   0.05438   0.04982  -0.0205   1.0000   0.0065
 -14.500  -1.0571   0.05064   0.04593  -0.0216   1.0000   0.0065
 -14.250  -1.0598   0.04742   0.04260  -0.0223   1.0000   0.0066
 -14.000  -1.0627   0.04434   0.03938  -0.0226   1.0000   0.0065
 -13.750  -1.0613   0.04191   0.03685  -0.0225   1.0000   0.0067
 -13.500  -1.0612   0.03944   0.03426  -0.0221   1.0000   0.0067
 -13.250  -1.0593   0.03725   0.03195  -0.0214   1.0000   0.0067
 -13.000  -1.0555   0.03534   0.02993  -0.0205   1.0000   0.0068
 -12.750  -1.0510   0.03355   0.02804  -0.0195   1.0000   0.0069
 -12.500  -1.0451   0.03194   0.02633  -0.0182   1.0000   0.0069
 -12.250  -1.0384   0.03044   0.02473  -0.0169   1.0000   0.0070
 -12.000  -1.0302   0.02911   0.02332  -0.0154   1.0000   0.0071
 -11.750  -1.0208   0.02789   0.02200  -0.0139   1.0000   0.0072
 -11.500  -1.0118   0.02667   0.02070  -0.0123   1.0000   0.0072
 -11.250  -1.0006   0.02562   0.01957  -0.0106   1.0000   0.0074
 -11.000  -0.9889   0.02464   0.01852  -0.0090   1.0000   0.0075
 -10.750  -0.9771   0.02367   0.01748  -0.0072   1.0000   0.0075
 -10.500  -0.9636   0.02283   0.01657  -0.0055   1.0000   0.0077
 -10.250  -0.9447   0.02199   0.01565  -0.0049   0.9486   0.0078
 -10.000  -0.9318   0.02130   0.01481  -0.0027   0.8960   0.0079
  -9.750  -0.9229   0.02064   0.01401   0.0004   0.8675   0.0080
  -9.500  -0.9111   0.02007   0.01334   0.0030   0.8460   0.0082
  -9.250  -0.8971   0.01952   0.01268   0.0053   0.8278   0.0082
  -9.000  -0.8798   0.01899   0.01206   0.0070   0.8118   0.0085
  -8.750  -0.8611   0.01849   0.01147   0.0084   0.7967   0.0087
  -8.500  -0.8417   0.01799   0.01089   0.0098   0.7830   0.0089
  -8.250  -0.8217   0.01751   0.01031   0.0111   0.7696   0.0091
  -8.000  -0.8008   0.01706   0.00978   0.0123   0.7565   0.0094
  -7.750  -0.7792   0.01661   0.00925   0.0134   0.7437   0.0097
  -7.500  -0.7571   0.01620   0.00875   0.0144   0.7317   0.0100
  -7.250  -0.7350   0.01576   0.00823   0.0154   0.7194   0.0104
  -7.000  -0.7120   0.01536   0.00779   0.0163   0.7074   0.0111
  -6.750  -0.6882   0.01504   0.00740   0.0170   0.6959   0.0118
  -6.250  -0.6403   0.01434   0.00660   0.0185   0.6724   0.0137
  -6.000  -0.6158   0.01405   0.00623   0.0192   0.6612   0.0151
  -5.750  -0.5912   0.01372   0.00587   0.0198   0.6493   0.0167
  -5.500  -0.5663   0.01343   0.00554   0.0204   0.6383   0.0192
  -5.000  -0.5161   0.01285   0.00492   0.0215   0.6154   0.0293
  -4.750  -0.4911   0.01255   0.00462   0.0221   0.6046   0.0399
  -4.500  -0.4665   0.01221   0.00433   0.0226   0.5930   0.0568
  -4.250  -0.4425   0.01178   0.00403   0.0233   0.5824   0.0872
  -4.000  -0.4194   0.01129   0.00371   0.0240   0.5716   0.1340
  -3.750  -0.3965   0.01075   0.00342   0.0248   0.5610   0.1938
  -3.500  -0.3737   0.01024   0.00316   0.0255   0.5508   0.2605
  -3.250  -0.3502   0.00981   0.00295   0.0262   0.5400   0.3233
  -3.000  -0.3260   0.00945   0.00278   0.0269   0.5302   0.3768
  -2.750  -0.3019   0.00912   0.00262   0.0275   0.5193   0.4303
  -2.500  -0.2778   0.00879   0.00249   0.0283   0.5090   0.4868
  -2.250  -0.2527   0.00857   0.00238   0.0288   0.4991   0.5308
  -2.000  -0.2263   0.00843   0.00230   0.0292   0.4887   0.5604
  -1.750  -0.1996   0.00833   0.00223   0.0296   0.4781   0.5866
  -1.500  -0.1729   0.00824   0.00217   0.0299   0.4677   0.6124
  -1.250  -0.1461   0.00815   0.00213   0.0302   0.4582   0.6395
  -1.000  -0.1193   0.00810   0.00210   0.0306   0.4477   0.6655
  -0.750  -0.0919   0.00806   0.00210   0.0309   0.4375   0.6888
  -0.500  -0.0644   0.00806   0.00210   0.0311   0.4282   0.7083
  -0.250  -0.0365   0.00807   0.00211   0.0312   0.4179   0.7249
   0.000  -0.0086   0.00811   0.00213   0.0314   0.4085   0.7395
   0.250   0.0195   0.00816   0.00215   0.0315   0.3988   0.7525
   0.500   0.0476   0.00821   0.00218   0.0315   0.3900   0.7649
   0.750   0.0756   0.00828   0.00222   0.0316   0.3802   0.7754
   1.000   0.1039   0.00834   0.00226   0.0316   0.3718   0.7854
   1.250   0.1319   0.00843   0.00231   0.0317   0.3630   0.7946
   1.500   0.1602   0.00850   0.00236   0.0317   0.3547   0.8033
   1.750   0.1881   0.00860   0.00244   0.0318   0.3462   0.8116
   2.000   0.2162   0.00869   0.00250   0.0319   0.3389   0.8204
   2.250   0.2439   0.00879   0.00259   0.0320   0.3308   0.8288
   2.500   0.2718   0.00890   0.00267   0.0320   0.3235   0.8373
   2.750   0.2996   0.00900   0.00277   0.0322   0.3164   0.8435
   3.000   0.3273   0.00913   0.00287   0.0322   0.3101   0.8499
   3.250   0.3554   0.00923   0.00295   0.0322   0.3033   0.8559
   3.500   0.3828   0.00937   0.00307   0.0323   0.2962   0.8607
   3.750   0.4105   0.00948   0.00318   0.0324   0.2906   0.8661
   4.000   0.4382   0.00961   0.00328   0.0324   0.2847   0.8718
   4.250   0.4654   0.00976   0.00342   0.0325   0.2788   0.8764
   4.500   0.4928   0.00988   0.00355   0.0326   0.2733   0.8812
   4.750   0.5199   0.01002   0.00368   0.0327   0.2671   0.8865
   5.000   0.5468   0.01019   0.00383   0.0328   0.2618   0.8919
   5.250   0.5738   0.01031   0.00398   0.0330   0.2571   0.8965
   5.500   0.6002   0.01047   0.00414   0.0333   0.2514   0.9021
   5.750   0.6262   0.01067   0.00432   0.0335   0.2461   0.9082
   6.000   0.6528   0.01080   0.00448   0.0337   0.2413   0.9126
   6.250   0.6789   0.01097   0.00466   0.0340   0.2364   0.9174
   6.500   0.7044   0.01119   0.00486   0.0343   0.2311   0.9225
   6.750   0.7306   0.01134   0.00503   0.0345   0.2266   0.9271
   7.000   0.7567   0.01152   0.00524   0.0347   0.2215   0.9312
   7.250   0.7817   0.01175   0.00546   0.0351   0.2166   0.9361
   7.500   0.8069   0.01193   0.00566   0.0354   0.2122   0.9414
   7.750   0.8334   0.01214   0.00589   0.0355   0.2068   0.9454
   8.000   0.8588   0.01241   0.00615   0.0356   0.2012   0.9501
   8.250   0.8841   0.01261   0.00638   0.0359   0.1964   0.9556
   8.500   0.9117   0.01287   0.00665   0.0355   0.1910   0.9597
   8.750   0.9392   0.01320   0.00697   0.0351   0.1862   0.9640
   9.000   0.9665   0.01344   0.00725   0.0349   0.1820   0.9689
   9.250   0.9961   0.01374   0.00758   0.0340   0.1770   0.9725
   9.750   1.0555   0.01443   0.00831   0.0321   0.1680   0.9802
  10.000   1.0849   0.01479   0.00869   0.0311   0.1628   0.9837
  10.250   1.1153   0.01525   0.00915   0.0298   0.1581   0.9867
  10.500   1.1461   0.01561   0.00956   0.0285   0.1538   0.9901
  10.750   1.1749   0.01606   0.01002   0.0274   0.1485   0.9944
  11.000   1.2034   0.01657   0.01056   0.0263   0.1440   0.9993
  11.250   1.2163   0.01692   0.01095   0.0283   0.1405   1.0000
  11.500   1.2261   0.01735   0.01139   0.0308   0.1366   1.0000
  11.750   1.2314   0.01790   0.01194   0.0338   0.1327   1.0000
  12.000   1.2408   0.01842   0.01251   0.0360   0.1296   1.0000
  12.250   1.2507   0.01907   0.01320   0.0378   0.1259   1.0000
  12.500   1.2588   0.01994   0.01408   0.0394   0.1216   1.0000
  12.750   1.2685   0.02083   0.01501   0.0406   0.1181   1.0000
  13.000   1.2784   0.02180   0.01602   0.0416   0.1141   1.0000
  13.250   1.2854   0.02304   0.01728   0.0426   0.1100   1.0000
  13.500   1.2932   0.02431   0.01860   0.0433   0.1067   1.0000
  13.750   1.3007   0.02569   0.02003   0.0439   0.1027   1.0000
  14.000   1.3044   0.02744   0.02180   0.0443   0.0989   1.0000
  14.250   1.3096   0.02915   0.02357   0.0446   0.0960   1.0000
  14.500   1.3133   0.03105   0.02552   0.0448   0.0922   1.0000
  14.750   1.3134   0.03337   0.02787   0.0447   0.0888   1.0000
  15.000   1.3140   0.03571   0.03028   0.0446   0.0859   1.0000
  15.250   1.3145   0.03813   0.03277   0.0443   0.0830   1.0000
  15.500   1.3119   0.04094   0.03563   0.0438   0.0805   1.0000
  15.750   1.3060   0.04419   0.03893   0.0431   0.0783   1.0000
  16.000   1.3035   0.04715   0.04197   0.0424   0.0763   1.0000
  16.250   1.3002   0.05029   0.04520   0.0416   0.0743   1.0000
  16.500   1.2947   0.05379   0.04878   0.0405   0.0725   1.0000
  16.750   1.2869   0.05769   0.05274   0.0391   0.0707   1.0000
  17.000   1.2760   0.06208   0.05719   0.0375   0.0689   1.0000
  17.250   1.2716   0.06571   0.06092   0.0361   0.0675   1.0000
  17.500   1.2650   0.06971   0.06500   0.0345   0.0657   1.0000
  17.750   1.2568   0.07402   0.06939   0.0328   0.0642   1.0000
  18.000   1.2465   0.07869   0.07414   0.0308   0.0627   1.0000
  18.250   1.2333   0.08387   0.07937   0.0285   0.0610   1.0000
<< Back to MH 92 15.49% (mh92-il)

Polar data table (+)

Polar graphs


<< Back to MH 92 15.49% (mh92-il)