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Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Bergey BW-3 (smoothed) (bw3-il)
Reynolds number: 100,000
Max Cl/Cd: 58.41 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bw3-il-100000-n5.txt
Download as CSV file: xf-bw3-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3532   0.10628   0.10094  -0.0185   1.0000   0.0502
  -7.500  -0.3509   0.10392   0.09863  -0.0181   1.0000   0.0509
  -7.250  -0.3489   0.10161   0.09638  -0.0177   1.0000   0.0516
  -7.000  -0.3441   0.09909   0.09392  -0.0181   1.0000   0.0524
  -6.750  -0.3384   0.09652   0.09140  -0.0189   1.0000   0.0536
  -6.500  -0.3319   0.09406   0.08900  -0.0203   1.0000   0.0547
  -6.250  -0.3235   0.09179   0.08678  -0.0231   1.0000   0.0558
  -6.000  -0.3118   0.08972   0.08473  -0.0277   1.0000   0.0562
  -5.500  -0.2998   0.08372   0.07886  -0.0273   1.0000   0.0572
  -5.250  -0.2970   0.08137   0.07657  -0.0253   1.0000   0.0581
  -5.000  -0.2740   0.07802   0.07320  -0.0292   0.9973   0.0592
  -4.750  -0.2402   0.07414   0.06927  -0.0358   0.9927   0.0603
  -4.500  -0.2050   0.07017   0.06522  -0.0428   0.9869   0.0610
  -4.250  -0.1592   0.06503   0.05992  -0.0536   0.9794   0.0556
  -4.000  -0.1311   0.06109   0.05594  -0.0573   0.9720   0.0523
  -3.500  -0.0406   0.05101   0.04547  -0.0750   0.9568   0.0480
  -3.250  -0.0008   0.04708   0.04136  -0.0807   0.9508   0.0479
  -3.000   0.0355   0.04412   0.03830  -0.0849   0.9446   0.0493
  -2.750   0.0711   0.04208   0.03619  -0.0881   0.9396   0.0524
  -2.500   0.1122   0.03860   0.03247  -0.0930   0.9335   0.0536
  -2.250   0.1624   0.03333   0.02668  -0.0995   0.9297   0.0565
  -2.000   0.1930   0.03302   0.02643  -0.1008   0.9245   0.0598
  -1.750   0.2317   0.03020   0.02329  -0.1037   0.9189   0.0628
  -1.500   0.2712   0.02804   0.02086  -0.1066   0.9147   0.0680
  -1.250   0.3114   0.02598   0.01845  -0.1093   0.9111   0.0735
  -1.000   0.3451   0.02479   0.01707  -0.1106   0.9040   0.0793
  -0.750   0.3860   0.02304   0.01481  -0.1131   0.8993   0.0884
  -0.500   0.4265   0.02246   0.01427  -0.1160   0.8954   0.0941
  -0.250   0.4614   0.02143   0.01282  -0.1171   0.8871   0.1019
   0.000   0.5005   0.02071   0.01209  -0.1196   0.8813   0.1061
   0.250   0.5366   0.02012   0.01126  -0.1211   0.8730   0.1129
   0.500   0.5757   0.01938   0.01035  -0.1233   0.8649   0.1163
   0.750   0.6095   0.01898   0.00994  -0.1245   0.8536   0.1203
   1.000   0.6466   0.01856   0.00940  -0.1261   0.8424   0.1248
   1.250   0.6813   0.01819   0.00890  -0.1272   0.8303   0.1270
   1.500   0.7119   0.01792   0.00859  -0.1275   0.8175   0.1292
   1.750   0.7444   0.01769   0.00843  -0.1284   0.8057   0.1335
   2.000   0.7787   0.01751   0.00824  -0.1295   0.7946   0.1372
   2.250   0.8075   0.01740   0.00816  -0.1294   0.7816   0.1393
   2.500   0.8380   0.01732   0.00810  -0.1297   0.7687   0.1418
   2.750   0.8710   0.01716   0.00802  -0.1305   0.7529   0.1445
   3.000   0.9017   0.01701   0.00787  -0.1305   0.7285   0.1496
   3.250   0.9282   0.01694   0.00772  -0.1295   0.6951   0.1550
   3.500   0.9546   0.01691   0.00765  -0.1286   0.6596   0.1585
   3.750   0.9801   0.01697   0.00765  -0.1276   0.6155   0.1624
   4.000   1.0041   0.01719   0.00769  -0.1263   0.5607   0.1674
   4.250   1.0238   0.01774   0.00780  -0.1241   0.4732   0.1723
   4.500   1.0395   0.01877   0.00821  -0.1216   0.3662   0.1802
   4.750   1.0519   0.02036   0.00901  -0.1189   0.2212   0.1910
   5.000   1.0620   0.02259   0.01024  -0.1162   0.0883   0.2028
   5.250   1.0881   0.02347   0.01127  -0.1162   0.0750   0.2627
   5.500   1.1409   0.02404   0.01277  -0.1225   0.0660   1.0000
   5.750   1.1597   0.02503   0.01378  -0.1208   0.0613   1.0000
   6.000   1.1768   0.02617   0.01493  -0.1188   0.0580   1.0000
   6.250   1.1951   0.02717   0.01602  -0.1169   0.0557   1.0000
   6.500   1.2129   0.02826   0.01716  -0.1150   0.0533   1.0000
   6.750   1.2303   0.02942   0.01833  -0.1132   0.0506   1.0000
   7.000   1.2469   0.03090   0.01973  -0.1113   0.0483   1.0000
   7.250   1.2665   0.03234   0.02120  -0.1099   0.0467   1.0000
   7.500   1.2882   0.03370   0.02265  -0.1087   0.0454   1.0000
   7.750   1.3106   0.03520   0.02425  -0.1077   0.0440   1.0000
   8.000   1.3326   0.03669   0.02587  -0.1067   0.0423   1.0000
   8.250   1.3532   0.03816   0.02741  -0.1056   0.0404   1.0000
   8.500   1.3741   0.03991   0.02918  -0.1048   0.0390   1.0000
   8.750   1.3976   0.04253   0.03183  -0.1045   0.0379   1.0000
   9.000   1.4163   0.04455   0.03421  -0.1029   0.0373   1.0000
   9.250   1.4327   0.04680   0.03684  -0.1010   0.0365   1.0000
   9.500   1.4459   0.04909   0.03951  -0.0988   0.0354   1.0000
   9.750   1.4571   0.05138   0.04213  -0.0965   0.0342   1.0000
  10.000   1.4665   0.05382   0.04486  -0.0941   0.0333   1.0000
  10.250   1.4738   0.05646   0.04781  -0.0915   0.0325   1.0000
  10.500   1.4783   0.05932   0.05096  -0.0887   0.0321   1.0000
  10.750   1.4799   0.06226   0.05418  -0.0858   0.0318   1.0000
  11.000   1.4790   0.06531   0.05748  -0.0827   0.0315   1.0000
  11.250   1.4731   0.06849   0.06093  -0.0792   0.0313   1.0000
  11.500   1.4619   0.07161   0.06428  -0.0752   0.0311   1.0000
  11.750   1.4487   0.07490   0.06780  -0.0716   0.0309   1.0000
  12.000   1.4352   0.07847   0.07157  -0.0688   0.0307   1.0000
  12.250   1.4172   0.08259   0.07593  -0.0665   0.0306   1.0000
  12.500   1.3988   0.08717   0.08073  -0.0652   0.0305   1.0000
  12.750   1.3767   0.09237   0.08618  -0.0650   0.0305   1.0000
  13.000   1.3486   0.09878   0.09289  -0.0661   0.0307   1.0000
  13.250   1.3228   0.10573   0.10007  -0.0686   0.0307   1.0000
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