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GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 511 AIRFOIL (goe511-il)
Reynolds number: 500,000
Max Cl/Cd: 71.83 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe511-il-500000.txt
Download as CSV file: xf-goe511-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 511 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1224   0.09810   0.09556  -0.1211   0.9478   0.0342
 -10.750   0.1372   0.09474   0.09219  -0.1242   0.9458   0.0352
 -10.500   0.1259   0.08748   0.08492  -0.1327   0.9437   0.0370
 -10.250   0.1565   0.08485   0.08228  -0.1351   0.9425   0.0374
 -10.000   0.1860   0.08182   0.07923  -0.1391   0.9411   0.0378
  -9.750   0.2459   0.06160   0.05909  -0.1512   0.9265   0.0419
  -9.500   0.2755   0.05865   0.05612  -0.1533   0.9240   0.0422
  -9.250   0.2797   0.05723   0.05472  -0.1512   0.9155   0.0425
  -9.000   0.2979   0.05450   0.05196  -0.1534   0.9095   0.0430
  -8.750   0.3067   0.05225   0.04971  -0.1539   0.9008   0.0437
  -8.500   0.3145   0.04933   0.04676  -0.1556   0.8921   0.0450
  -8.250   0.2671   0.05866   0.05602  -0.1632   0.9043   0.0439
  -8.000   0.2603   0.05619   0.05353  -0.1629   0.8925   0.0445
  -7.750   0.2346   0.05354   0.05085  -0.1594   0.8785   0.0464
  -7.500   0.1927   0.04715   0.04431  -0.1569   0.8626   0.0479
  -7.250   0.1989   0.04587   0.04298  -0.1545   0.8460   0.0481
  -7.000   0.2115   0.04462   0.04163  -0.1533   0.8226   0.0486
  -6.750   0.2228   0.04291   0.03970  -0.1522   0.7832   0.0491
  -6.500   0.1660   0.03280   0.02885  -0.1448   0.7552   0.0541
  -6.250   0.1763   0.03218   0.02809  -0.1418   0.7258   0.0544
  -6.000   0.1833   0.03173   0.02750  -0.1381   0.7026   0.0548
  -5.750   0.1867   0.03099   0.02662  -0.1339   0.6823   0.0553
  -5.500   0.1865   0.03028   0.02578  -0.1287   0.6625   0.0561
  -5.250   0.1804   0.02890   0.02419  -0.1226   0.6434   0.0574
  -5.000   0.1181   0.01919   0.01261  -0.1049   0.6385   0.0422
  -4.750   0.1259   0.01873   0.01192  -0.1006   0.6191   0.0420
  -4.500   0.1351   0.01811   0.01110  -0.0967   0.6008   0.0421
  -4.250   0.1469   0.01741   0.01021  -0.0933   0.5854   0.0422
  -4.000   0.1619   0.01682   0.00947  -0.0906   0.5725   0.0424
  -3.750   0.1783   0.01635   0.00887  -0.0881   0.5618   0.0426
  -3.500   0.1972   0.01598   0.00843  -0.0862   0.5522   0.0432
  -3.250   0.2161   0.01577   0.00813  -0.0843   0.5436   0.0439
  -3.000   0.2369   0.01547   0.00776  -0.0827   0.5361   0.0443
  -2.750   0.2572   0.01523   0.00741  -0.0810   0.5287   0.0448
  -2.500   0.2786   0.01500   0.00710  -0.0796   0.5221   0.0453
  -2.250   0.3000   0.01477   0.00681  -0.0781   0.5154   0.0458
  -2.000   0.3206   0.01464   0.00657  -0.0764   0.5084   0.0463
  -1.750   0.3424   0.01453   0.00640  -0.0750   0.5025   0.0470
  -1.500   0.3640   0.01437   0.00621  -0.0736   0.4966   0.0474
  -1.250   0.3840   0.01406   0.00589  -0.0720   0.4907   0.0484
  -1.000   0.4045   0.01396   0.00576  -0.0704   0.4852   0.0493
  -0.750   0.4251   0.01386   0.00568  -0.0688   0.4797   0.0507
  -0.500   0.4451   0.01380   0.00559  -0.0672   0.4740   0.0522
  -0.250   0.4647   0.01382   0.00554  -0.0654   0.4680   0.0532
   0.000   0.4844   0.01364   0.00540  -0.0637   0.4628   0.0552
   0.250   0.5041   0.01358   0.00534  -0.0620   0.4569   0.0573
   0.500   0.5230   0.01361   0.00531  -0.0601   0.4510   0.0595
   0.750   0.5422   0.01357   0.00527  -0.0583   0.4454   0.0637
   1.000   0.5611   0.01354   0.00527  -0.0565   0.4393   0.0705
   1.250   0.5765   0.01342   0.00528  -0.0540   0.4334   0.1180
   1.500   0.5942   0.01341   0.00552  -0.0521   0.4280   0.2113
   1.750   0.6150   0.01352   0.00565  -0.0507   0.4223   0.2284
   2.000   0.6348   0.01371   0.00578  -0.0492   0.4164   0.2399
   2.250   0.6531   0.01387   0.00592  -0.0474   0.4110   0.2489
   2.500   0.6742   0.01400   0.00605  -0.0462   0.4060   0.2575
   2.750   0.6932   0.01413   0.00618  -0.0446   0.4009   0.2661
   3.000   0.7120   0.01434   0.00633  -0.0430   0.3959   0.2734
   3.250   0.7323   0.01449   0.00647  -0.0417   0.3917   0.2802
   3.500   0.7526   0.01461   0.00663  -0.0404   0.3873   0.2890
   3.750   0.7722   0.01479   0.00678  -0.0390   0.3832   0.2964
   4.000   0.7901   0.01498   0.00696  -0.0373   0.3789   0.3043
   4.250   0.8101   0.01518   0.00714  -0.0360   0.3752   0.3117
   4.500   0.8304   0.01530   0.00731  -0.0348   0.3718   0.3208
   4.750   1.0242   0.01491   0.00850  -0.0717   0.3633   0.9769
   5.000   1.1303   0.01578   0.00923  -0.0888   0.3580   1.0000
   5.250   1.1473   0.01598   0.00943  -0.0870   0.3559   1.0000
   5.500   1.1641   0.01621   0.00965  -0.0851   0.3535   1.0000
   5.750   1.1809   0.01644   0.00987  -0.0833   0.3510   1.0000
   6.000   1.1978   0.01670   0.01011  -0.0816   0.3486   1.0000
   6.250   1.2137   0.01700   0.01036  -0.0797   0.3456   1.0000
   6.500   1.2319   0.01735   0.01064  -0.0783   0.3426   1.0000
   6.750   1.2492   0.01761   0.01092  -0.0767   0.3407   1.0000
   7.000   1.2643   0.01788   0.01122  -0.0747   0.3381   1.0000
   7.250   1.2818   0.01815   0.01151  -0.0732   0.3362   1.0000
   7.500   1.2977   0.01845   0.01181  -0.0715   0.3335   1.0000
   7.750   1.3141   0.01878   0.01213  -0.0698   0.3313   1.0000
   8.000   1.3306   0.01914   0.01247  -0.0683   0.3291   1.0000
   8.250   1.3484   0.01953   0.01281  -0.0670   0.3263   1.0000
   8.500   1.3662   0.01988   0.01317  -0.0657   0.3241   1.0000
   8.750   1.3823   0.02022   0.01356  -0.0641   0.3225   1.0000
   9.000   1.3978   0.02059   0.01397  -0.0625   0.3206   1.0000
   9.250   1.4128   0.02098   0.01440  -0.0609   0.3184   1.0000
   9.500   1.4284   0.02138   0.01482  -0.0594   0.3162   1.0000
   9.750   1.4442   0.02180   0.01524  -0.0579   0.3143   1.0000
  10.000   1.4599   0.02225   0.01569  -0.0565   0.3123   1.0000
  10.250   1.4769   0.02271   0.01613  -0.0554   0.3099   1.0000
  10.500   1.4942   0.02316   0.01659  -0.0543   0.3076   1.0000
  10.750   1.5087   0.02364   0.01714  -0.0528   0.3063   1.0000
  11.000   1.5217   0.02418   0.01774  -0.0512   0.3044   1.0000
  11.250   1.5354   0.02473   0.01835  -0.0497   0.3025   1.0000
  11.500   1.5492   0.02529   0.01895  -0.0483   0.3004   1.0000
  11.750   1.5630   0.02587   0.01957  -0.0469   0.2986   1.0000
  12.000   1.5758   0.02650   0.02023  -0.0455   0.2965   1.0000
  12.250   1.5903   0.02711   0.02084  -0.0443   0.2943   1.0000
  12.500   1.6073   0.02766   0.02138  -0.0435   0.2916   1.0000
  12.750   1.6166   0.02849   0.02231  -0.0418   0.2900   1.0000
  13.000   1.6264   0.02934   0.02325  -0.0402   0.2879   1.0000
  13.250   1.6351   0.03027   0.02426  -0.0387   0.2852   1.0000
  13.500   1.6446   0.03121   0.02524  -0.0373   0.2826   1.0000
  13.750   1.6520   0.03230   0.02634  -0.0357   0.2791   1.0000
  14.000   1.6614   0.03332   0.02735  -0.0345   0.2755   1.0000
  14.250   1.6671   0.03465   0.02881  -0.0331   0.2728   1.0000
  14.500   1.6743   0.03593   0.03019  -0.0319   0.2697   1.0000
  14.750   1.6807   0.03731   0.03162  -0.0307   0.2664   1.0000
  15.000   1.6841   0.03893   0.03324  -0.0295   0.2623   1.0000
  15.250   1.6896   0.04045   0.03483  -0.0284   0.2591   1.0000
  15.500   1.6938   0.04219   0.03669  -0.0275   0.2549   1.0000
  15.750   1.6959   0.04413   0.03868  -0.0265   0.2503   1.0000
  16.000   1.6931   0.04652   0.04106  -0.0254   0.2452   1.0000
  16.250   1.6968   0.04844   0.04311  -0.0247   0.2409   1.0000
  16.500   1.6931   0.05109   0.04580  -0.0239   0.2348   1.0000
  16.750   1.6872   0.05401   0.04876  -0.0231   0.2292   1.0000
  17.000   1.6822   0.05694   0.05177  -0.0225   0.2226   1.0000
  17.250   1.6695   0.06071   0.05556  -0.0218   0.2160   1.0000
  17.500   1.6610   0.06413   0.05904  -0.0214   0.2092   1.0000
  17.750   1.6418   0.06877   0.06370  -0.0209   0.2020   1.0000
  18.000   1.6290   0.07279   0.06777  -0.0207   0.1956   1.0000
  18.250   1.6074   0.07783   0.07280  -0.0205   0.1895   1.0000
  18.500   1.5973   0.08163   0.07668  -0.0205   0.1848   1.0000
  18.750   1.5820   0.08609   0.08116  -0.0206   0.1802   1.0000
  19.000   1.5679   0.09041   0.08549  -0.0207   0.1758   1.0000
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