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MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 84 13.69% (mh84-il)
Reynolds number: 100,000
Max Cl/Cd: 40.4 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh84-il-100000.txt
Download as CSV file: xf-mh84-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 84  13.69%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2615   0.12289   0.11846  -0.0041   1.0000   0.0893
  -9.750  -0.2687   0.12140   0.11705  -0.0088   1.0000   0.0921
  -9.500  -0.2716   0.11877   0.11452  -0.0126   1.0000   0.0929
  -9.250  -0.2421   0.11341   0.10919  -0.0104   1.0000   0.0947
  -9.000  -0.2282   0.11028   0.10613  -0.0112   1.0000   0.0971
  -8.750  -0.2198   0.10740   0.10333  -0.0134   1.0000   0.1004
  -8.500  -0.2371   0.10647   0.10256  -0.0214   1.0000   0.1036
  -8.250  -0.2190   0.10177   0.09795  -0.0219   1.0000   0.1048
  -8.000  -0.1955   0.09813   0.09438  -0.0215   1.0000   0.1072
  -7.750  -0.1764   0.09493   0.09125  -0.0256   0.9760   0.1109
  -7.500  -0.1763   0.09148   0.08779  -0.0427   0.9363   0.1166
  -7.250  -0.1394   0.08660   0.08285  -0.0392   0.9181   0.1186
  -7.000  -0.1244   0.08403   0.08021  -0.0384   0.8938   0.1215
  -6.750  -0.1216   0.08191   0.07807  -0.0388   0.8701   0.1256
  -6.500  -0.1485   0.07995   0.07611  -0.0500   0.8473   0.1303
  -6.250  -0.1319   0.07693   0.07307  -0.0436   0.8321   0.1317
  -6.000  -0.1173   0.07473   0.07081  -0.0402   0.8173   0.1347
  -5.500  -0.1258   0.03981   0.03428  -0.0822   0.8012   0.0654
  -5.250  -0.1047   0.03597   0.02993  -0.0838   0.7872   0.0653
  -5.000  -0.0820   0.03267   0.02600  -0.0844   0.7751   0.0657
  -4.750  -0.0587   0.03039   0.02346  -0.0839   0.7630   0.0666
  -4.500  -0.0329   0.02857   0.02141  -0.0837   0.7495   0.0681
  -4.250  -0.0072   0.02685   0.01928  -0.0829   0.7385   0.0705
  -4.000   0.0198   0.02537   0.01748  -0.0825   0.7253   0.0753
  -3.750   0.0473   0.02442   0.01625  -0.0818   0.7130   0.0824
  -3.500   0.0733   0.02335   0.01512  -0.0808   0.7020   0.0907
  -3.250   0.1010   0.02249   0.01424  -0.0805   0.6888   0.1055
  -3.000   0.1278   0.02185   0.01352  -0.0795   0.6788   0.1291
  -2.750   0.1555   0.02140   0.01319  -0.0792   0.6654   0.1623
  -2.500   0.1828   0.02126   0.01304  -0.0786   0.6540   0.1965
  -2.250   0.2095   0.02109   0.01290  -0.0779   0.6427   0.2264
  -2.000   0.2372   0.02092   0.01269  -0.0775   0.6303   0.2557
  -1.750   0.2639   0.02064   0.01237  -0.0765   0.6207   0.2822
  -1.500   0.2918   0.02047   0.01221  -0.0762   0.6077   0.3096
  -1.250   0.3192   0.02021   0.01184  -0.0755   0.5980   0.3371
  -1.000   0.3466   0.01998   0.01171  -0.0750   0.5859   0.3647
  -0.750   0.3742   0.01984   0.01150  -0.0745   0.5754   0.3964
  -0.500   0.4013   0.01958   0.01133  -0.0738   0.5647   0.4293
  -0.250   0.4283   0.01945   0.01130  -0.0732   0.5539   0.4688
   0.000   0.4548   0.01918   0.01111  -0.0723   0.5442   0.5202
   0.250   0.4805   0.01899   0.01121  -0.0714   0.5332   0.5928
   0.500   0.5023   0.01847   0.01105  -0.0690   0.5247   0.7202
   0.750   0.5318   0.01802   0.01091  -0.0683   0.5133   1.0000
   1.000   0.5619   0.01821   0.01069  -0.0683   0.5046   1.0000
   1.250   0.5905   0.01859   0.01094  -0.0685   0.4933   1.0000
   1.500   0.6195   0.01880   0.01082  -0.0681   0.4853   1.0000
   1.750   0.6473   0.01922   0.01118  -0.0682   0.4740   1.0000
   2.000   0.6760   0.01945   0.01110  -0.0678   0.4664   1.0000
   2.250   0.7033   0.01992   0.01156  -0.0678   0.4556   1.0000
   2.500   0.7319   0.02016   0.01152  -0.0674   0.4482   1.0000
   2.750   0.7587   0.02068   0.01206  -0.0674   0.4379   1.0000
   3.000   0.7870   0.02096   0.01211  -0.0670   0.4306   1.0000
   3.250   0.8136   0.02153   0.01268  -0.0669   0.4212   1.0000
   3.500   0.8414   0.02184   0.01282  -0.0666   0.4136   1.0000
   3.750   0.8680   0.02243   0.01336  -0.0664   0.4055   1.0000
   4.000   0.8949   0.02287   0.01374  -0.0662   0.3976   1.0000
   4.250   0.9227   0.02332   0.01400  -0.0659   0.3912   1.0000
   4.500   0.9478   0.02398   0.01475  -0.0657   0.3825   1.0000
   4.750   0.9757   0.02432   0.01491  -0.0654   0.3765   1.0000
   5.000   1.0003   0.02514   0.01580  -0.0652   0.3690   1.0000
   5.250   1.0264   0.02566   0.01627  -0.0649   0.3621   1.0000
   5.500   1.0548   0.02611   0.01650  -0.0647   0.3569   1.0000
   5.750   1.0767   0.02708   0.01770  -0.0644   0.3492   1.0000
   6.000   1.1032   0.02758   0.01811  -0.0641   0.3434   1.0000
   6.250   1.1296   0.02826   0.01868  -0.0638   0.3383   1.0000
   6.500   1.1508   0.02930   0.01992  -0.0634   0.3313   1.0000
   6.750   1.1769   0.02982   0.02037  -0.0631   0.3261   1.0000
   7.000   1.2033   0.03056   0.02099  -0.0629   0.3216   1.0000
   7.250   1.2212   0.03190   0.02260  -0.0624   0.3152   1.0000
   7.500   1.2457   0.03255   0.02323  -0.0620   0.3101   1.0000
   7.750   1.2749   0.03301   0.02348  -0.0618   0.3062   1.0000
   8.000   1.2877   0.03485   0.02568  -0.0611   0.3006   1.0000
   8.250   1.3074   0.03600   0.02693  -0.0606   0.2956   1.0000
   8.500   1.3340   0.03649   0.02732  -0.0603   0.2916   1.0000
   8.750   1.3550   0.03774   0.02860  -0.0598   0.2876   1.0000
   9.000   1.3611   0.04003   0.03123  -0.0588   0.2825   1.0000
   9.250   1.3791   0.04129   0.03256  -0.0582   0.2784   1.0000
   9.500   1.4065   0.04178   0.03296  -0.0579   0.2750   1.0000
   9.750   1.4216   0.04354   0.03481  -0.0573   0.2715   1.0000
  10.000   1.4020   0.04772   0.03945  -0.0553   0.2671   1.0000
  10.250   1.3988   0.05046   0.04236  -0.0540   0.2633   1.0000
  10.500   1.4275   0.05075   0.04259  -0.0537   0.2601   1.0000
  10.750   1.4728   0.05033   0.04199  -0.0542   0.2574   1.0000
  11.000   0.8381   0.15131   0.14435  -0.0994   0.2920   1.0000
  11.250   0.8706   0.15456   0.14761  -0.0984   0.2901   1.0000
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