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Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Bergey BW-3 (smoothed) (bw3-il)
Reynolds number: 100,000
Max Cl/Cd: 67.6 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bw3-il-100000.txt
Download as CSV file: xf-bw3-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3642   0.11541   0.11004  -0.0192   1.0000   0.0651
  -8.000  -0.3711   0.11549   0.11021  -0.0199   1.0000   0.0654
  -7.750  -0.3697   0.11538   0.11018  -0.0243   1.0000   0.0656
  -7.500  -0.3597   0.10831   0.10314  -0.0207   1.0000   0.0661
  -7.250  -0.3507   0.10359   0.09843  -0.0187   1.0000   0.0670
  -7.000  -0.3439   0.10050   0.09538  -0.0183   1.0000   0.0680
  -6.750  -0.3376   0.09773   0.09267  -0.0183   1.0000   0.0693
  -6.500  -0.3313   0.09521   0.09018  -0.0189   1.0000   0.0707
  -6.250  -0.3244   0.09279   0.08781  -0.0199   1.0000   0.0724
  -6.000  -0.3152   0.09095   0.08603  -0.0226   1.0000   0.0745
  -5.750  -0.2877   0.09280   0.08784  -0.0371   1.0000   0.0759
  -5.500  -0.2900   0.08772   0.08288  -0.0324   1.0000   0.0764
  -5.250  -0.2924   0.08382   0.07905  -0.0275   1.0000   0.0772
  -5.000  -0.2909   0.08113   0.07642  -0.0252   1.0000   0.0781
  -4.750  -0.2865   0.07888   0.07421  -0.0243   1.0000   0.0793
  -4.500  -0.2792   0.07668   0.07203  -0.0244   1.0000   0.0809
  -4.250  -0.2680   0.07448   0.06984  -0.0257   1.0000   0.0828
  -4.000  -0.2475   0.07251   0.06782  -0.0298   1.0000   0.0859
  -3.750  -0.1940   0.07181   0.06685  -0.0442   1.0000   0.0880
  -3.500  -0.1933   0.06758   0.06273  -0.0409   1.0000   0.0887
  -3.250  -0.1889   0.06441   0.05963  -0.0385   1.0000   0.0900
  -3.000  -0.1762   0.06203   0.05726  -0.0383   1.0000   0.0923
  -2.750  -0.1503   0.05970   0.05488  -0.0415   0.9994   0.0965
  -2.500  -0.0743   0.05682   0.05162  -0.0566   0.9951   0.1018
  -2.250  -0.0486   0.05291   0.04776  -0.0583   0.9908   0.1039
  -2.000  -0.0090   0.05014   0.04491  -0.0630   0.9859   0.1091
  -1.750   0.0451   0.04727   0.04179  -0.0711   0.9814   0.1171
  -1.500   0.0813   0.04479   0.03924  -0.0745   0.9755   0.1234
  -1.250   0.1275   0.04227   0.03650  -0.0801   0.9701   0.1316
  -1.000   0.1711   0.04010   0.03416  -0.0846   0.9649   0.1453
  -0.750   0.2105   0.03819   0.03207  -0.0880   0.9583   0.1593
  -0.500   0.2506   0.03606   0.02987  -0.0915   0.9539   0.1778
  -0.250   0.2856   0.03452   0.02821  -0.0938   0.9463   0.2056
   0.000   0.3269   0.03280   0.02641  -0.0972   0.9417   0.2510
   0.250   0.3530   0.03118   0.02488  -0.0975   0.9333   0.3047
   0.500   0.3889   0.02913   0.02293  -0.0992   0.9284   0.3887
   0.750   0.4178   0.02763   0.02145  -0.0992   0.9195   0.4589
   1.000   0.4701   0.02605   0.01969  -0.1037   0.9138   0.4760
   1.250   0.5463   0.02580   0.01812  -0.1112   0.9050   0.2277
   1.500   0.5976   0.02452   0.01658  -0.1148   0.8990   0.2107
   1.750   0.6553   0.02320   0.01511  -0.1199   0.8955   0.2110
   2.000   0.6917   0.02269   0.01454  -0.1211   0.8843   0.2081
   2.250   0.7537   0.02156   0.01338  -0.1273   0.8798   0.2085
   2.500   0.7912   0.02124   0.01308  -0.1288   0.8677   0.2136
   2.750   0.8383   0.02070   0.01257  -0.1320   0.8573   0.2161
   3.000   0.8906   0.01979   0.01173  -0.1357   0.8391   0.2195
   3.250   0.9430   0.01869   0.01067  -0.1386   0.8123   0.2279
   3.500   0.9734   0.01831   0.01038  -0.1379   0.7851   0.2368
   3.750   1.0050   0.01787   0.00998  -0.1372   0.7564   0.2459
   4.000   1.0333   0.01750   0.00965  -0.1360   0.7226   0.2572
   4.250   1.0599   0.01719   0.00936  -0.1343   0.6794   0.2753
   4.500   1.1087   0.01640   0.00917  -0.1376   0.5498   1.0000
   4.750   1.1081   0.01838   0.00954  -0.1309   0.3213   1.0000
   5.000   1.1102   0.02124   0.01090  -0.1262   0.1345   1.0000
   5.250   1.1258   0.02273   0.01209  -0.1236   0.1145   1.0000
   5.500   1.1436   0.02390   0.01321  -0.1214   0.1038   1.0000
   5.750   1.1596   0.02527   0.01455  -0.1190   0.0980   1.0000
   6.000   1.1782   0.02653   0.01580  -0.1169   0.0932   1.0000
   6.250   1.1975   0.02807   0.01719  -0.1152   0.0885   1.0000
   6.500   1.2210   0.02990   0.01892  -0.1143   0.0845   1.0000
   6.750   1.2475   0.03143   0.02053  -0.1136   0.0819   1.0000
   7.000   1.2755   0.03320   0.02237  -0.1132   0.0801   1.0000
   7.250   1.3032   0.03513   0.02437  -0.1128   0.0779   1.0000
   7.500   1.3292   0.03728   0.02655  -0.1124   0.0749   1.0000
   7.750   1.3558   0.04013   0.02953  -0.1121   0.0735   1.0000
   8.000   1.3797   0.04287   0.03256  -0.1111   0.0734   1.0000
   8.250   1.4008   0.04538   0.03545  -0.1093   0.0740   1.0000
   8.500   1.4195   0.04855   0.03895  -0.1076   0.0738   1.0000
   8.750   1.4353   0.05225   0.04298  -0.1057   0.0733   1.0000
   9.000   1.4384   0.05517   0.04691  -0.1005   0.0775   1.0000
   9.250   1.4449   0.06060   0.05288  -0.0973   0.0827   1.0000
   9.500   1.3515   0.05542   0.04883  -0.0790   0.0906   1.0000
  11.250   1.1200   0.14602   0.14135  -0.1108   0.1940   1.0000
  11.500   0.8820   0.14195   0.13751  -0.0878   0.1965   1.0000
  11.750   0.8866   0.14507   0.14064  -0.0872   0.1925   1.0000
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