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Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Bergey BW-3 (smoothed) (bw3-il)
Reynolds number: 50,000
Max Cl/Cd: 46.73 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bw3-il-50000.txt
Download as CSV file: xf-bw3-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Bergey BW-3  (smoothed)                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3485   0.10977   0.10238  -0.0182   1.0000   0.1094
  -7.250  -0.3463   0.10776   0.10045  -0.0186   1.0000   0.1115
  -7.000  -0.3429   0.10649   0.09927  -0.0206   1.0000   0.1134
  -6.750  -0.3375   0.10682   0.09968  -0.0259   1.0000   0.1145
  -6.500  -0.3300   0.10286   0.09580  -0.0260   1.0000   0.1153
  -6.250  -0.3231   0.09764   0.09061  -0.0228   1.0000   0.1171
  -6.000  -0.3156   0.09441   0.08744  -0.0222   1.0000   0.1196
  -5.750  -0.3077   0.09181   0.08490  -0.0229   1.0000   0.1226
  -5.500  -0.2966   0.09025   0.08339  -0.0262   1.0000   0.1267
  -5.250  -0.2798   0.08926   0.08242  -0.0326   1.0000   0.1289
  -5.000  -0.2795   0.08456   0.07783  -0.0278   1.0000   0.1312
  -4.750  -0.2725   0.08181   0.07513  -0.0269   1.0000   0.1348
  -4.500  -0.2593   0.07989   0.07323  -0.0294   1.0000   0.1398
  -4.250  -0.2367   0.07842   0.07169  -0.0357   1.0000   0.1432
  -4.000  -0.2347   0.07469   0.06804  -0.0323   1.0000   0.1456
  -3.750  -0.2240   0.07213   0.06550  -0.0322   1.0000   0.1502
  -3.500  -0.1911   0.07084   0.06407  -0.0401   1.0000   0.1576
  -3.250  -0.1883   0.06719   0.06053  -0.0368   1.0000   0.1615
  -3.000  -0.1574   0.06566   0.05887  -0.0428   1.0000   0.1727
  -2.750  -0.1511   0.06238   0.05566  -0.0402   1.0000   0.1789
  -2.500  -0.1254   0.06018   0.05338  -0.0439   1.0000   0.1899
  -2.250  -0.0989   0.05826   0.05136  -0.0472   1.0000   0.2035
  -2.000  -0.0757   0.05621   0.04925  -0.0493   1.0000   0.2184
  -1.750  -0.0585   0.05361   0.04667  -0.0495   1.0000   0.2355
  -1.500  -0.0357   0.05183   0.04483  -0.0511   1.0000   0.2657
  -1.250  -0.0180   0.04962   0.04263  -0.0510   1.0000   0.2984
  -1.000  -0.0039   0.04720   0.04029  -0.0498   1.0000   0.3352
  -0.250   0.0229   0.04001   0.03344  -0.0400   1.0000   0.5447
   0.000   0.0374   0.03772   0.03121  -0.0378   1.0000   0.5971
   0.250   0.0606   0.03597   0.02945  -0.0378   1.0000   0.6343
   0.500   0.0894   0.03462   0.02804  -0.0394   1.0000   0.6633
   0.750   0.1358   0.03428   0.02746  -0.0462   1.0000   0.6505
   1.000   0.2104   0.03676   0.02909  -0.0616   1.0000   0.4872
   1.250   0.2579   0.03777   0.02941  -0.0678   1.0000   0.3719
   1.500   0.2904   0.03790   0.02912  -0.0701   1.0000   0.3340
   1.750   0.3193   0.03811   0.02898  -0.0715   1.0000   0.3082
   2.000   0.3718   0.03841   0.02887  -0.0772   0.9930   0.2979
   2.250   0.4356   0.03862   0.02876  -0.0849   0.9807   0.2944
   2.500   0.4942   0.03877   0.02865  -0.0917   0.9661   0.2933
   2.750   0.5534   0.03896   0.02861  -0.0983   0.9512   0.2948
   3.000   0.6097   0.03904   0.02867  -0.1045   0.9350   0.3029
   3.250   0.6674   0.03916   0.02881  -0.1105   0.9186   0.3072
   3.500   0.7239   0.03920   0.02898  -0.1162   0.9014   0.3171
   3.750   0.7810   0.03912   0.02921  -0.1217   0.8836   0.3371
   4.000   0.8392   0.03893   0.02936  -0.1271   0.8655   0.3604
   4.500   1.0100   0.03294   0.02469  -0.1395   0.8057   1.0000
   4.750   1.0821   0.02862   0.02046  -0.1395   0.7627   1.0000
   5.000   1.1149   0.02661   0.01851  -0.1352   0.7154   1.0000
   5.250   1.1327   0.02480   0.01658  -0.1278   0.6415   1.0000
   5.500   1.1387   0.02437   0.01559  -0.1194   0.4995   1.0000
   5.750   1.1302   0.02735   0.01653  -0.1116   0.2577   1.0000
   6.000   1.1371   0.03004   0.01838  -0.1080   0.1926   1.0000
   6.250   1.1528   0.03202   0.02006  -0.1056   0.1705   1.0000
   6.500   1.1748   0.03385   0.02171  -0.1041   0.1569   1.0000
   6.750   1.2037   0.03581   0.02340  -0.1037   0.1442   1.0000
   7.000   1.2382   0.03764   0.02541  -0.1038   0.1365   1.0000
   7.250   1.2762   0.04019   0.02780  -0.1049   0.1307   1.0000
   7.500   1.3060   0.04272   0.03059  -0.1046   0.1259   1.0000
   7.750   1.3323   0.04533   0.03354  -0.1038   0.1225   1.0000
   8.000   1.3570   0.04843   0.03703  -0.1027   0.1216   1.0000
   8.250   1.3774   0.05186   0.04095  -0.1011   0.1216   1.0000
   8.500   1.3928   0.05545   0.04501  -0.0989   0.1214   1.0000
   8.750   1.4040   0.05912   0.04914  -0.0965   0.1204   1.0000
   9.000   1.4101   0.06322   0.05376  -0.0936   0.1209   1.0000
   9.250   1.4115   0.06788   0.05894  -0.0905   0.1229   1.0000
   9.500   1.4098   0.07293   0.06442  -0.0876   0.1256   1.0000
   9.750   1.4160   0.07841   0.07010  -0.0859   0.1284   1.0000
  10.000   1.3854   0.08336   0.07577  -0.0811   0.1328   1.0000
  10.250   1.3433   0.08952   0.08236  -0.0772   0.1364   1.0000
  10.500   1.3102   0.09518   0.08821  -0.0745   0.1391   1.0000
  10.750   1.3162   0.10155   0.09467  -0.0744   0.1451   1.0000
  11.000   1.2434   0.11019   0.10350  -0.0769   0.1465   1.0000
  11.250   1.1758   0.12843   0.12177  -0.0901   0.1611   1.0000
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