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

AG36 (ag36-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AG36 (ag36-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag36-il-1000000.txt
Download as CSV file: xf-ag36-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG36                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4449   0.06978   0.06832  -0.0170   1.0000   0.0128
  -9.750  -0.4490   0.06520   0.06376  -0.0189   1.0000   0.0129
  -9.500  -0.4561   0.06021   0.05879  -0.0215   1.0000   0.0129
  -9.250  -0.4693   0.05363   0.05223  -0.0276   1.0000   0.0129
  -9.000  -0.4721   0.04672   0.04527  -0.0342   1.0000   0.0130
  -8.750  -0.4764   0.03774   0.03617  -0.0401   1.0000   0.0130
  -8.500  -0.4749   0.03160   0.02989  -0.0420   1.0000   0.0132
  -8.250  -0.5242   0.02585   0.02289  -0.0440   1.0000   0.0106
  -8.000  -0.5149   0.01946   0.01573  -0.0422   1.0000   0.0107
  -7.750  -0.4963   0.01724   0.01316  -0.0408   1.0000   0.0109
  -7.500  -0.4644   0.01530   0.01092  -0.0420   0.9983   0.0112
  -7.250  -0.4310   0.01391   0.00931  -0.0433   0.9963   0.0115
  -7.000  -0.3962   0.01321   0.00849  -0.0447   0.9946   0.0121
  -6.750  -0.3641   0.01184   0.00692  -0.0457   0.9919   0.0127
  -6.500  -0.3314   0.01076   0.00574  -0.0469   0.9888   0.0135
  -6.250  -0.2976   0.01027   0.00522  -0.0481   0.9853   0.0142
  -6.000  -0.2654   0.00980   0.00470  -0.0489   0.9801   0.0149
  -5.750  -0.2344   0.00935   0.00420  -0.0495   0.9725   0.0157
  -5.500  -0.2052   0.00902   0.00381  -0.0495   0.9625   0.0165
  -5.250  -0.1781   0.00842   0.00313  -0.0492   0.9505   0.0181
  -5.000  -0.1518   0.00817   0.00285  -0.0486   0.9353   0.0198
  -4.750  -0.1258   0.00796   0.00257  -0.0479   0.9173   0.0215
  -4.500  -0.0997   0.00773   0.00225  -0.0472   0.8948   0.0235
  -4.250  -0.0739   0.00752   0.00194  -0.0465   0.8668   0.0278
  -4.000  -0.0470   0.00741   0.00171  -0.0460   0.8445   0.0330
  -3.500   0.0077   0.00705   0.00138  -0.0456   0.8094   0.0763
  -3.250   0.0352   0.00681   0.00126  -0.0455   0.7927   0.1280
  -3.000   0.0627   0.00655   0.00116  -0.0454   0.7755   0.1968
  -2.750   0.0901   0.00630   0.00109  -0.0454   0.7569   0.2749
  -2.500   0.1175   0.00608   0.00104  -0.0454   0.7360   0.3564
  -2.250   0.1447   0.00580   0.00100  -0.0453   0.7096   0.4637
  -2.000   0.1706   0.00537   0.00096  -0.0451   0.6597   0.6359
  -1.750   0.1940   0.00504   0.00098  -0.0442   0.6143   0.8100
  -1.500   0.2139   0.00484   0.00103  -0.0419   0.5933   0.9380
  -1.250   0.2532   0.00489   0.00102  -0.0442   0.5759   0.9934
  -1.000   0.2857   0.00498   0.00102  -0.0453   0.5620   1.0000
  -0.750   0.3131   0.00508   0.00103  -0.0451   0.5500   1.0000
  -0.500   0.3406   0.00516   0.00105  -0.0450   0.5389   1.0000
  -0.250   0.3684   0.00524   0.00107  -0.0450   0.5284   1.0000
   0.000   0.3961   0.00533   0.00110  -0.0449   0.5185   1.0000
   0.250   0.4239   0.00542   0.00113  -0.0449   0.5079   1.0000
   0.500   0.4519   0.00549   0.00118  -0.0449   0.4974   1.0000
   0.750   0.4799   0.00558   0.00122  -0.0449   0.4863   1.0000
   1.000   0.5078   0.00567   0.00127  -0.0450   0.4744   1.0000
   1.250   0.5358   0.00576   0.00132  -0.0450   0.4595   1.0000
   1.500   0.5636   0.00588   0.00138  -0.0451   0.4421   1.0000
   1.750   0.5913   0.00603   0.00145  -0.0451   0.4220   1.0000
   2.000   0.6190   0.00618   0.00154  -0.0451   0.4024   1.0000
   2.250   0.6463   0.00638   0.00165  -0.0451   0.3781   1.0000
   2.500   0.6737   0.00658   0.00177  -0.0452   0.3545   1.0000
   2.750   0.7009   0.00682   0.00191  -0.0452   0.3283   1.0000
   3.000   0.7279   0.00708   0.00207  -0.0452   0.3032   1.0000
   3.250   0.7550   0.00733   0.00224  -0.0452   0.2797   1.0000
   3.500   0.7819   0.00761   0.00242  -0.0452   0.2540   1.0000
   3.750   0.8085   0.00793   0.00263  -0.0452   0.2259   1.0000
   4.000   0.8346   0.00833   0.00287  -0.0452   0.1933   1.0000
   4.250   0.8610   0.00868   0.00313  -0.0452   0.1682   1.0000
   4.500   0.8873   0.00903   0.00339  -0.0451   0.1456   1.0000
   4.750   0.9133   0.00943   0.00367  -0.0451   0.1235   1.0000
   5.000   0.9392   0.00981   0.00397  -0.0450   0.1033   1.0000
   5.250   0.9649   0.01024   0.00431  -0.0449   0.0837   1.0000
   5.500   0.9903   0.01069   0.00467  -0.0448   0.0652   1.0000
   5.750   1.0153   0.01119   0.00508  -0.0446   0.0478   1.0000
   6.000   1.0397   0.01178   0.00556  -0.0444   0.0311   1.0000
   6.250   1.0642   0.01233   0.00608  -0.0441   0.0212   1.0000
   6.500   1.0887   0.01288   0.00662  -0.0438   0.0159   1.0000
   6.750   1.1126   0.01351   0.00726  -0.0434   0.0125   1.0000
   7.000   1.1372   0.01399   0.00780  -0.0432   0.0110   1.0000
   7.250   1.1612   0.01454   0.00838  -0.0428   0.0098   1.0000
   7.500   1.1828   0.01545   0.00939  -0.0421   0.0085   1.0000
   7.750   1.2065   0.01597   0.00998  -0.0418   0.0081   1.0000
   8.000   1.2294   0.01659   0.01067  -0.0413   0.0075   1.0000
   8.250   1.2517   0.01726   0.01140  -0.0408   0.0071   1.0000
   8.500   1.2729   0.01803   0.01223  -0.0402   0.0067   1.0000
   8.750   1.2897   0.01932   0.01365  -0.0390   0.0062   1.0000
   9.000   1.3047   0.02074   0.01522  -0.0375   0.0059   1.0000
   9.250   1.3248   0.02148   0.01605  -0.0368   0.0057   1.0000
   9.500   1.3428   0.02239   0.01706  -0.0358   0.0056   1.0000
   9.750   1.3586   0.02349   0.01826  -0.0346   0.0054   1.0000
  10.000   1.3725   0.02470   0.01959  -0.0332   0.0053   1.0000
  10.250   1.3845   0.02600   0.02101  -0.0316   0.0052   1.0000
  10.500   1.3939   0.02738   0.02252  -0.0297   0.0051   1.0000
  10.750   1.3983   0.02881   0.02407  -0.0271   0.0050   1.0000
  11.000   1.4006   0.03039   0.02579  -0.0246   0.0049   1.0000
  11.250   1.4014   0.03224   0.02777  -0.0225   0.0049   1.0000
  11.500   1.4013   0.03436   0.03003  -0.0210   0.0048   1.0000
  11.750   1.3997   0.03687   0.03267  -0.0200   0.0048   1.0000
  12.000   1.3968   0.03980   0.03574  -0.0197   0.0047   1.0000
  12.250   1.3927   0.04313   0.03922  -0.0200   0.0047   1.0000
  12.500   1.3868   0.04700   0.04324  -0.0209   0.0046   1.0000
  12.750   1.3790   0.05146   0.04785  -0.0224   0.0046   1.0000
  13.000   1.3701   0.05646   0.05301  -0.0247   0.0046   1.0000
  13.250   1.3584   0.06202   0.05872  -0.0272   0.0046   1.0000
  13.500   1.3444   0.06807   0.06492  -0.0300   0.0046   1.0000
  13.750   1.3277   0.07461   0.07161  -0.0330   0.0046   1.0000
  14.000   1.3091   0.08169   0.07884  -0.0364   0.0046   1.0000
  14.250   1.2891   0.08928   0.08657  -0.0400   0.0046   1.0000
  14.500   1.2686   0.09734   0.09477  -0.0439   0.0046   1.0000
  14.750   1.2460   0.10608   0.10366  -0.0482   0.0047   1.0000
  15.000   1.2229   0.11532   0.11304  -0.0528   0.0047   1.0000
  15.250   1.2000   0.12481   0.12266  -0.0575   0.0047   1.0000
  15.500   1.1761   0.13486   0.13284  -0.0626   0.0048   1.0000
  15.750   1.1482   0.14650   0.14463  -0.0686   0.0049   1.0000
  16.000   1.1148   0.16044   0.15873  -0.0758   0.0050   1.0000
  16.250   0.8634   0.14771   0.14607  -0.0485   0.0055   1.0000
<< Back to AG36 (ag36-il)

Polar data table (+)

Polar graphs


<< Back to AG36 (ag36-il)