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MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 84 13.69% (mh84-il)
Reynolds number: 100,000
Max Cl/Cd: 48.18 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh84-il-100000-n5.txt
Download as CSV file: xf-mh84-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2857   0.12640   0.12178  -0.0031   1.0000   0.0577
 -10.250  -0.2808   0.12310   0.11854  -0.0054   1.0000   0.0580
  -9.750  -0.2771   0.11115   0.10661  -0.0113   1.0000   0.0363
  -9.500  -0.2632   0.10860   0.10412  -0.0117   1.0000   0.0356
  -9.000  -0.2580   0.09908   0.09471  -0.0178   0.9584   0.0319
  -8.750  -0.2410   0.09515   0.09072  -0.0218   0.9076   0.0314
  -8.500  -0.2331   0.09153   0.08703  -0.0239   0.8756   0.0310
  -8.250  -0.2292   0.08803   0.08348  -0.0254   0.8506   0.0305
  -8.000  -0.2284   0.08408   0.07949  -0.0271   0.8303   0.0302
  -7.750  -0.2290   0.07989   0.07527  -0.0291   0.8130   0.0298
  -7.500  -0.2332   0.07503   0.07039  -0.0317   0.7977   0.0293
  -7.250  -0.2677   0.06219   0.05753  -0.0423   0.7870   0.0279
  -7.000  -0.2842   0.04610   0.04100  -0.0619   0.7770   0.0271
  -6.750  -0.2773   0.03806   0.03219  -0.0700   0.7650   0.0271
  -6.500  -0.2590   0.03365   0.02708  -0.0728   0.7527   0.0275
  -6.250  -0.2371   0.03102   0.02396  -0.0737   0.7414   0.0284
  -6.000  -0.2123   0.02973   0.02252  -0.0740   0.7280   0.0295
  -5.750  -0.1875   0.02800   0.02040  -0.0743   0.7165   0.0311
  -5.500  -0.1616   0.02635   0.01838  -0.0744   0.7045   0.0324
  -5.250  -0.1354   0.02524   0.01714  -0.0743   0.6927   0.0335
  -5.000  -0.1090   0.02408   0.01573  -0.0739   0.6816   0.0349
  -4.750  -0.0816   0.02298   0.01441  -0.0738   0.6695   0.0366
  -4.500  -0.0550   0.02223   0.01354  -0.0735   0.6591   0.0390
  -4.250  -0.0273   0.02148   0.01269  -0.0734   0.6468   0.0427
  -4.000   0.0003   0.02077   0.01183  -0.0731   0.6363   0.0471
  -3.750   0.0283   0.02010   0.01107  -0.0730   0.6246   0.0528
  -3.500   0.0563   0.01952   0.01044  -0.0728   0.6139   0.0617
  -3.250   0.0844   0.01895   0.00982  -0.0727   0.6031   0.0757
  -3.000   0.1128   0.01847   0.00937  -0.0726   0.5919   0.0967
  -2.750   0.1409   0.01814   0.00902  -0.0724   0.5819   0.1225
  -2.500   0.1694   0.01792   0.00881  -0.0723   0.5704   0.1488
  -2.250   0.1975   0.01780   0.00858  -0.0720   0.5609   0.1748
  -2.000   0.2261   0.01767   0.00847  -0.0719   0.5494   0.1986
  -1.750   0.2541   0.01756   0.00829  -0.0715   0.5397   0.2205
  -1.500   0.2825   0.01745   0.00815  -0.0713   0.5288   0.2417
  -1.250   0.3106   0.01736   0.00798  -0.0710   0.5193   0.2627
  -1.000   0.3388   0.01727   0.00787  -0.0708   0.5086   0.2842
  -0.750   0.3668   0.01720   0.00775  -0.0705   0.4992   0.3071
  -0.500   0.3949   0.01714   0.00767  -0.0702   0.4891   0.3320
  -0.250   0.4227   0.01708   0.00761  -0.0699   0.4797   0.3595
   0.000   0.4503   0.01702   0.00758  -0.0695   0.4700   0.3925
   0.250   0.4782   0.01697   0.00758  -0.0692   0.4610   0.4329
   0.500   0.5058   0.01690   0.00760  -0.0689   0.4515   0.4846
   0.750   0.5327   0.01682   0.00766  -0.0684   0.4428   0.5524
   1.000   0.5581   0.01668   0.00774  -0.0674   0.4338   0.6416
   1.250   0.5803   0.01643   0.00774  -0.0656   0.4261   0.7642
   1.500   0.6115   0.01625   0.00769  -0.0655   0.4165   1.0000
   1.750   0.6398   0.01650   0.00772  -0.0654   0.4088   1.0000
   2.000   0.6681   0.01677   0.00786  -0.0654   0.3997   1.0000
   2.250   0.6959   0.01704   0.00791  -0.0652   0.3926   1.0000
   2.500   0.7239   0.01733   0.00814  -0.0652   0.3837   1.0000
   2.750   0.7515   0.01762   0.00826  -0.0650   0.3765   1.0000
   3.000   0.7791   0.01794   0.00849  -0.0648   0.3686   1.0000
   3.250   0.8064   0.01826   0.00870  -0.0647   0.3611   1.0000
   3.500   0.8336   0.01860   0.00891  -0.0645   0.3545   1.0000
   3.750   0.8606   0.01895   0.00922  -0.0643   0.3469   1.0000
   4.000   0.8874   0.01930   0.00942  -0.0640   0.3407   1.0000
   4.250   0.9141   0.01970   0.00980  -0.0639   0.3336   1.0000
   4.500   0.9406   0.02008   0.01011  -0.0636   0.3271   1.0000
   4.750   0.9668   0.02048   0.01039  -0.0633   0.3215   1.0000
   5.000   0.9929   0.02092   0.01085  -0.0631   0.3147   1.0000
   5.250   1.0187   0.02133   0.01119  -0.0628   0.3089   1.0000
   5.500   1.0443   0.02179   0.01159  -0.0625   0.3036   1.0000
   5.750   1.0696   0.02228   0.01210  -0.0623   0.2974   1.0000
   6.000   1.0948   0.02273   0.01250  -0.0619   0.2922   1.0000
   6.250   1.1197   0.02324   0.01294  -0.0616   0.2873   1.0000
   6.500   1.1441   0.02379   0.01356  -0.0613   0.2817   1.0000
   6.750   1.1685   0.02430   0.01404  -0.0609   0.2768   1.0000
   7.000   1.1928   0.02483   0.01445  -0.0605   0.2727   1.0000
   7.250   1.2158   0.02547   0.01522  -0.0601   0.2674   1.0000
   7.500   1.2390   0.02607   0.01584  -0.0596   0.2627   1.0000
   7.750   1.2622   0.02663   0.01635  -0.0592   0.2588   1.0000
   8.000   1.2847   0.02731   0.01705  -0.0587   0.2548   1.0000
   8.250   1.3058   0.02804   0.01788  -0.0582   0.2501   1.0000
   8.500   1.3273   0.02871   0.01857  -0.0576   0.2461   1.0000
   8.750   1.3492   0.02935   0.01917  -0.0571   0.2428   1.0000
   9.000   1.3693   0.03017   0.02005  -0.0564   0.2392   1.0000
   9.250   1.3873   0.03107   0.02107  -0.0557   0.2352   1.0000
   9.500   1.4058   0.03187   0.02193  -0.0549   0.2315   1.0000
   9.750   1.4250   0.03261   0.02266  -0.0542   0.2284   1.0000
  10.000   1.4438   0.03345   0.02348  -0.0535   0.2255   1.0000
  10.250   1.4562   0.03464   0.02487  -0.0524   0.2221   1.0000
  10.500   1.4691   0.03575   0.02610  -0.0514   0.2189   1.0000
  10.750   1.4821   0.03675   0.02715  -0.0502   0.2159   1.0000
  11.000   1.4960   0.03765   0.02804  -0.0491   0.2134   1.0000
  11.250   1.5089   0.03872   0.02913  -0.0481   0.2109   1.0000
  11.500   1.5075   0.04061   0.03124  -0.0465   0.2081   1.0000
  11.750   1.5089   0.04251   0.03329  -0.0455   0.2054   1.0000
  12.000   1.5133   0.04430   0.03518  -0.0447   0.2029   1.0000
  12.250   1.5210   0.04587   0.03681  -0.0441   0.2006   1.0000
  12.500   1.5345   0.04706   0.03799  -0.0435   0.1985   1.0000
  12.750   1.5354   0.04936   0.04041  -0.0431   0.1963   1.0000
  13.000   1.5165   0.05365   0.04498  -0.0434   0.1937   1.0000
  13.250   1.4996   0.05816   0.04971  -0.0443   0.1911   1.0000
  13.500   1.4889   0.06223   0.05393  -0.0451   0.1887   1.0000
  13.750   1.4891   0.06514   0.05691  -0.0456   0.1866   1.0000
  14.000   1.5033   0.06638   0.05815  -0.0453   0.1849   1.0000
  14.250   1.4820   0.07224   0.06419  -0.0472   0.1827   1.0000
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