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Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Bergey BW-3 (smoothed) (bw3-il)
Reynolds number: 50,000
Max Cl/Cd: 46.03 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bw3-il-50000-n5.txt
Download as CSV file: xf-bw3-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3489   0.11093   0.10339  -0.0194   1.0000   0.0806
  -7.500  -0.3467   0.10860   0.10113  -0.0191   1.0000   0.0818
  -7.250  -0.3435   0.10624   0.09885  -0.0193   1.0000   0.0831
  -7.000  -0.3385   0.10389   0.09657  -0.0202   1.0000   0.0845
  -6.750  -0.3331   0.10183   0.09459  -0.0218   1.0000   0.0859
  -6.500  -0.3259   0.10004   0.09287  -0.0244   1.0000   0.0868
  -6.250  -0.3161   0.09819   0.09105  -0.0278   1.0000   0.0873
  -6.000  -0.3038   0.09617   0.08906  -0.0315   1.0000   0.0876
  -5.500  -0.2910   0.08845   0.08149  -0.0289   1.0000   0.0894
  -5.250  -0.2844   0.08543   0.07854  -0.0277   1.0000   0.0913
  -5.000  -0.2757   0.08291   0.07607  -0.0280   1.0000   0.0939
  -4.750  -0.2649   0.08058   0.07378  -0.0293   1.0000   0.0962
  -4.500  -0.2506   0.07839   0.07159  -0.0320   1.0000   0.0985
  -4.250  -0.2291   0.07649   0.06961  -0.0369   1.0000   0.1002
  -4.000  -0.2057   0.07434   0.06737  -0.0416   1.0000   0.1007
  -3.750  -0.1837   0.07189   0.06484  -0.0450   1.0000   0.1009
  -3.250  -0.1688   0.06543   0.05853  -0.0419   1.0000   0.1043
  -3.000  -0.1436   0.06286   0.05591  -0.0448   0.9983   0.1097
  -2.750  -0.0815   0.06023   0.05291  -0.0569   0.9933   0.1144
  -2.500  -0.0306   0.05461   0.04691  -0.0650   0.9890   0.0877
  -2.250  -0.0092   0.05218   0.04462  -0.0656   0.9829   0.0961
  -2.000   0.0329   0.04917   0.04140  -0.0710   0.9768   0.0960
  -1.750   0.0784   0.04578   0.03769  -0.0768   0.9711   0.0912
  -1.500   0.1178   0.04351   0.03521  -0.0807   0.9648   0.0957
  -1.250   0.1589   0.04114   0.03250  -0.0847   0.9580   0.0985
  -1.000   0.2015   0.03881   0.02982  -0.0887   0.9526   0.1025
  -0.750   0.2345   0.03733   0.02821  -0.0906   0.9451   0.1096
  -0.500   0.2774   0.03548   0.02588  -0.0940   0.9396   0.1157
  -0.250   0.3106   0.03424   0.02453  -0.0957   0.9321   0.1227
   0.000   0.3532   0.03285   0.02278  -0.0989   0.9273   0.1310
   0.250   0.3859   0.03190   0.02164  -0.1001   0.9186   0.1363
   0.500   0.4277   0.03092   0.02037  -0.1029   0.9131   0.1452
   0.750   0.4624   0.03021   0.01949  -0.1044   0.9045   0.1490
   1.000   0.5052   0.02959   0.01854  -0.1071   0.8980   0.1570
   1.250   0.5435   0.02893   0.01783  -0.1093   0.8896   0.1605
   1.500   0.5890   0.02831   0.01704  -0.1125   0.8822   0.1647
   1.750   0.6304   0.02795   0.01649  -0.1149   0.8725   0.1721
   2.000   0.6811   0.02723   0.01576  -0.1190   0.8644   0.1763
   2.250   0.7200   0.02690   0.01545  -0.1209   0.8524   0.1797
   2.500   0.7629   0.02652   0.01505  -0.1233   0.8417   0.1867
   2.750   0.8059   0.02607   0.01477  -0.1259   0.8303   0.1954
   3.000   0.8402   0.02596   0.01477  -0.1268   0.8162   0.2005
   3.250   0.8755   0.02581   0.01479  -0.1278   0.8021   0.2063
   3.500   0.9105   0.02570   0.01486  -0.1288   0.7877   0.2147
   3.750   0.9453   0.02558   0.01501  -0.1296   0.7722   0.2301
   4.000   0.9809   0.02505   0.01472  -0.1297   0.7467   0.2509
   4.250   1.0102   0.02435   0.01429  -0.1281   0.7048   0.2904
   4.500   1.0457   0.02328   0.01394  -0.1281   0.6543   1.0000
   4.750   1.0663   0.02332   0.01383  -0.1251   0.6017   1.0000
   5.000   1.0853   0.02358   0.01375  -0.1219   0.5292   1.0000
   5.250   1.0982   0.02450   0.01387  -0.1179   0.4055   1.0000
   5.500   1.1020   0.02681   0.01489  -0.1138   0.2262   1.0000
   5.750   1.1095   0.02941   0.01649  -0.1109   0.1271   1.0000
   6.000   1.1242   0.03115   0.01806  -0.1088   0.1076   1.0000
   6.250   1.1392   0.03276   0.01959  -0.1067   0.0970   1.0000
   6.500   1.1549   0.03422   0.02111  -0.1047   0.0901   1.0000
   6.750   1.1690   0.03592   0.02278  -0.1025   0.0857   1.0000
   7.000   1.1870   0.03730   0.02434  -0.1007   0.0813   1.0000
   7.250   1.2051   0.03881   0.02594  -0.0990   0.0764   1.0000
   7.500   1.2256   0.04063   0.02769  -0.0978   0.0728   1.0000
   7.750   1.2527   0.04233   0.02949  -0.0972   0.0706   1.0000
   8.000   1.2799   0.04409   0.03145  -0.0967   0.0676   1.0000
   8.250   1.3047   0.04602   0.03356  -0.0961   0.0641   1.0000
   8.500   1.3294   0.04825   0.03588  -0.0957   0.0615   1.0000
   8.750   1.3559   0.05107   0.03880  -0.0957   0.0600   1.0000
   9.000   1.3787   0.05428   0.04222  -0.0951   0.0589   1.0000
   9.250   1.3922   0.05691   0.04535  -0.0929   0.0578   1.0000
   9.500   1.4018   0.05973   0.04870  -0.0904   0.0562   1.0000
   9.750   1.4089   0.06278   0.05219  -0.0879   0.0548   1.0000
  10.000   1.4129   0.06608   0.05591  -0.0852   0.0538   1.0000
  10.250   1.4130   0.06972   0.05995  -0.0822   0.0534   1.0000
  10.500   1.4087   0.07343   0.06405  -0.0791   0.0532   1.0000
  10.750   1.3995   0.07727   0.06824  -0.0758   0.0530   1.0000
  11.000   1.3841   0.08109   0.07238  -0.0721   0.0530   1.0000
  11.250   1.3652   0.08504   0.07662  -0.0688   0.0531   1.0000
  11.500   1.3429   0.08957   0.08142  -0.0666   0.0532   1.0000
  11.750   1.3187   0.09477   0.08688  -0.0657   0.0534   1.0000
  12.000   1.2925   0.10082   0.09318  -0.0664   0.0537   1.0000
  12.250   1.2644   0.10796   0.10053  -0.0689   0.0542   1.0000
  12.500   1.2354   0.11640   0.10915  -0.0731   0.0547   1.0000
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