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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.83 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh83-il-1000000.txt
Download as CSV file: xf-mh83-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2621   0.09790   0.09512  -0.0083   0.6214   0.0142
  -8.750  -0.2554   0.09487   0.09206  -0.0098   0.6116   0.0146
  -8.500  -0.2503   0.09144   0.08862  -0.0116   0.6032   0.0149
  -8.250  -0.2585   0.08458   0.08176  -0.0159   0.5984   0.0159
  -8.000  -0.2593   0.07981   0.07699  -0.0186   0.5916   0.0160
  -7.750  -0.2595   0.07564   0.07282  -0.0208   0.5841   0.0160
  -7.500  -0.2679   0.07119   0.06839  -0.0226   0.5775   0.0162
  -7.250  -0.2658   0.06876   0.06596  -0.0238   0.5694   0.0163
  -7.000  -0.3376   0.02286   0.01841  -0.0642   0.5867   0.0135
  -6.750  -0.3128   0.02071   0.01592  -0.0648   0.5764   0.0135
  -6.500  -0.2867   0.01905   0.01399  -0.0651   0.5660   0.0135
  -6.250  -0.2598   0.01770   0.01241  -0.0652   0.5565   0.0136
  -6.000  -0.2324   0.01657   0.01108  -0.0653   0.5465   0.0136
  -5.750  -0.2046   0.01561   0.00995  -0.0653   0.5369   0.0137
  -5.250  -0.1482   0.01412   0.00818  -0.0653   0.5169   0.0140
  -5.000  -0.1197   0.01350   0.00743  -0.0653   0.5076   0.0141
  -4.750  -0.0910   0.01302   0.00686  -0.0652   0.4986   0.0144
  -4.500  -0.0623   0.01261   0.00635  -0.0652   0.4897   0.0148
  -4.250  -0.0334   0.01216   0.00581  -0.0651   0.4806   0.0151
  -4.000  -0.0045   0.01173   0.00528  -0.0650   0.4716   0.0154
  -3.750   0.0246   0.01137   0.00484  -0.0650   0.4624   0.0157
  -3.500   0.0538   0.01113   0.00452  -0.0649   0.4543   0.0160
  -3.250   0.0827   0.01054   0.00386  -0.0650   0.4461   0.0166
  -3.000   0.1119   0.01028   0.00355  -0.0650   0.4382   0.0171
  -2.750   0.1412   0.01008   0.00330  -0.0649   0.4305   0.0177
  -2.500   0.1705   0.00992   0.00307  -0.0649   0.4225   0.0184
  -2.250   0.1999   0.00977   0.00287  -0.0649   0.4149   0.0190
  -2.000   0.2292   0.00957   0.00260  -0.0649   0.4066   0.0201
  -1.750   0.2586   0.00943   0.00244  -0.0649   0.4001   0.0217
  -1.500   0.2879   0.00932   0.00229  -0.0649   0.3928   0.0241
  -1.250   0.3174   0.00920   0.00215  -0.0649   0.3866   0.0290
  -1.000   0.3466   0.00890   0.00202  -0.0650   0.3801   0.0746
  -0.750   0.3758   0.00880   0.00198  -0.0651   0.3731   0.1093
  -0.500   0.4050   0.00868   0.00195  -0.0652   0.3674   0.1421
  -0.250   0.4341   0.00858   0.00194  -0.0653   0.3609   0.1893
   0.000   0.4633   0.00849   0.00196  -0.0654   0.3552   0.2386
   0.250   0.4924   0.00839   0.00198  -0.0655   0.3501   0.2907
   0.500   0.5214   0.00830   0.00202  -0.0656   0.3445   0.3545
   0.750   0.5502   0.00817   0.00209  -0.0657   0.3395   0.4351
   1.250   0.6077   0.00791   0.00222  -0.0658   0.3301   0.6096
   1.500   0.6355   0.00780   0.00233  -0.0657   0.3246   0.7133
   1.750   0.6580   0.00736   0.00240  -0.0641   0.3217   0.8919
   2.000   0.6907   0.00733   0.00242  -0.0648   0.3176   1.0000
   2.250   0.7197   0.00746   0.00248  -0.0648   0.3135   1.0000
   2.500   0.7484   0.00763   0.00258  -0.0649   0.3088   1.0000
   2.750   0.7776   0.00771   0.00264  -0.0649   0.3063   1.0000
   3.000   0.8065   0.00782   0.00271  -0.0650   0.3029   1.0000
   3.250   0.8353   0.00796   0.00279  -0.0650   0.2993   1.0000
   3.500   0.8639   0.00813   0.00291  -0.0650   0.2955   1.0000
   3.750   0.8925   0.00828   0.00303  -0.0651   0.2924   1.0000
   4.000   0.9214   0.00838   0.00312  -0.0651   0.2902   1.0000
   4.250   0.9500   0.00850   0.00322  -0.0652   0.2874   1.0000
   4.500   0.9785   0.00865   0.00334  -0.0652   0.2843   1.0000
   4.750   1.0068   0.00883   0.00348  -0.0653   0.2810   1.0000
   5.000   1.0348   0.00905   0.00366  -0.0653   0.2776   1.0000
   5.250   1.0633   0.00916   0.00377  -0.0653   0.2760   1.0000
   5.500   1.0917   0.00928   0.00390  -0.0654   0.2739   1.0000
   5.750   1.1200   0.00942   0.00403  -0.0654   0.2713   1.0000
   6.000   1.1480   0.00960   0.00418  -0.0654   0.2687   1.0000
   6.250   1.1757   0.00980   0.00437  -0.0655   0.2659   1.0000
   6.500   1.2029   0.01008   0.00461  -0.0654   0.2625   1.0000
   6.750   1.2310   0.01020   0.00475  -0.0655   0.2612   1.0000
   7.000   1.2590   0.01033   0.00491  -0.0655   0.2592   1.0000
   7.250   1.2868   0.01049   0.00507  -0.0655   0.2570   1.0000
   7.500   1.3142   0.01067   0.00526  -0.0655   0.2548   1.0000
   7.750   1.3413   0.01089   0.00547  -0.0655   0.2524   1.0000
   8.000   1.3678   0.01117   0.00574  -0.0655   0.2493   1.0000
   8.250   1.3947   0.01140   0.00598  -0.0654   0.2470   1.0000
   8.500   1.4221   0.01155   0.00617  -0.0655   0.2454   1.0000
   8.750   1.4492   0.01173   0.00637  -0.0654   0.2436   1.0000
   9.000   1.4760   0.01192   0.00659  -0.0654   0.2413   1.0000
   9.250   1.5024   0.01215   0.00683  -0.0654   0.2388   1.0000
   9.500   1.5281   0.01245   0.00711  -0.0653   0.2361   1.0000
   9.750   1.5530   0.01281   0.00748  -0.0651   0.2330   1.0000
  10.000   1.5797   0.01297   0.00769  -0.0650   0.2315   1.0000
  10.250   1.6059   0.01316   0.00793  -0.0650   0.2295   1.0000
  10.500   1.6316   0.01339   0.00819  -0.0649   0.2271   1.0000
  10.750   1.6567   0.01366   0.00848  -0.0647   0.2244   1.0000
  11.000   1.6806   0.01402   0.00884  -0.0644   0.2214   1.0000
  11.250   1.7042   0.01439   0.00923  -0.0641   0.2185   1.0000
  11.500   1.7295   0.01459   0.00949  -0.0640   0.2165   1.0000
  11.750   1.7540   0.01484   0.00980  -0.0637   0.2140   1.0000
  12.000   1.7773   0.01517   0.01014  -0.0634   0.2111   1.0000
  12.250   1.7991   0.01559   0.01057  -0.0629   0.2078   1.0000
  12.500   1.8204   0.01601   0.01102  -0.0624   0.2043   1.0000
  12.750   1.8436   0.01627   0.01135  -0.0621   0.2013   1.0000
  13.000   1.8643   0.01667   0.01177  -0.0615   0.1972   1.0000
  13.250   1.8813   0.01726   0.01236  -0.0605   0.1930   1.0000
  13.500   1.9002   0.01769   0.01285  -0.0596   0.1901   1.0000
  13.750   1.9166   0.01815   0.01336  -0.0585   0.1864   1.0000
  14.000   1.9245   0.01884   0.01408  -0.0563   0.1827   1.0000
  14.250   1.9290   0.01983   0.01509  -0.0541   0.1781   1.0000
  14.500   1.9391   0.02068   0.01599  -0.0528   0.1734   1.0000
  14.750   1.9434   0.02203   0.01736  -0.0514   0.1686   1.0000
  15.000   1.9484   0.02347   0.01884  -0.0503   0.1645   1.0000
  15.250   1.9542   0.02498   0.02040  -0.0495   0.1596   1.0000
  15.500   1.9539   0.02710   0.02255  -0.0487   0.1552   1.0000
  15.750   1.9556   0.02917   0.02467  -0.0482   0.1505   1.0000
  16.000   1.9545   0.03160   0.02716  -0.0478   0.1460   1.0000
  16.250   1.9457   0.03490   0.03048  -0.0476   0.1408   1.0000
  16.500   1.9423   0.03782   0.03348  -0.0476   0.1363   1.0000
  16.750   1.9298   0.04176   0.03747  -0.0479   0.1318   1.0000
  17.000   1.9175   0.04585   0.04163  -0.0484   0.1278   1.0000
  17.250   1.9051   0.05006   0.04591  -0.0490   0.1238   1.0000
  17.500   1.8841   0.05555   0.05146  -0.0503   0.1196   1.0000
  17.750   1.8672   0.06077   0.05677  -0.0516   0.1161   1.0000
  18.000   1.8489   0.06633   0.06242  -0.0532   0.1123   1.0000
  18.250   1.8238   0.07303   0.06918  -0.0554   0.1085   1.0000
  18.500   1.8039   0.07921   0.07546  -0.0576   0.1056   1.0000
  18.750   1.7841   0.08557   0.08190  -0.0599   0.1020   1.0000
  19.000   1.7595   0.09276   0.08917  -0.0627   0.0987   1.0000
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