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Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Bergey BW-3 (smoothed) (bw3-il)
Reynolds number: 200,000
Max Cl/Cd: 74.66 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bw3-il-200000.txt
Download as CSV file: xf-bw3-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3722   0.11339   0.10954  -0.0175   1.0000   0.0406
  -8.250  -0.3786   0.11276   0.10898  -0.0186   1.0000   0.0408
  -8.000  -0.3829   0.11164   0.10792  -0.0202   1.0000   0.0409
  -7.750  -0.3702   0.10560   0.10188  -0.0177   1.0000   0.0413
  -7.500  -0.3619   0.10201   0.09832  -0.0166   1.0000   0.0419
  -7.250  -0.3577   0.09950   0.09584  -0.0158   1.0000   0.0426
  -7.000  -0.3519   0.09699   0.09338  -0.0160   1.0000   0.0434
  -6.750  -0.3455   0.09448   0.09091  -0.0165   1.0000   0.0449
  -6.500  -0.3388   0.09203   0.08850  -0.0178   1.0000   0.0466
  -6.250  -0.3268   0.09069   0.08720  -0.0245   1.0000   0.0480
  -6.000  -0.3141   0.08936   0.08589  -0.0319   1.0000   0.0483
  -5.750  -0.3194   0.08576   0.08237  -0.0268   1.0000   0.0486
  -5.500  -0.3235   0.08323   0.07989  -0.0227   1.0000   0.0489
  -5.250  -0.3178   0.08059   0.07728  -0.0215   0.9993   0.0494
  -5.000  -0.2873   0.07688   0.07354  -0.0264   0.9963   0.0509
  -4.750  -0.2510   0.07307   0.06969  -0.0335   0.9924   0.0532
  -4.500  -0.1795   0.06804   0.06447  -0.0535   0.9876   0.0568
  -4.250  -0.1634   0.06428   0.06074  -0.0526   0.9833   0.0578
  -4.000  -0.1329   0.06105   0.05748  -0.0564   0.9785   0.0596
  -3.750  -0.0909   0.05757   0.05393  -0.0634   0.9740   0.0629
  -3.500  -0.0219   0.05303   0.04912  -0.0787   0.9678   0.0661
  -3.250   0.0020   0.04953   0.04564  -0.0797   0.9643   0.0671
  -3.000   0.0316   0.04691   0.04300  -0.0821   0.9576   0.0693
  -2.750   0.1108   0.04449   0.04006  -0.0956   0.9543   0.0760
  -2.500   0.1313   0.03998   0.03565  -0.0966   0.9485   0.0770
  -2.250   0.1624   0.03735   0.03303  -0.0987   0.9444   0.0787
  -2.000   0.2230   0.03583   0.03104  -0.1056   0.9418   0.0877
  -1.750   0.2526   0.03178   0.02694  -0.1078   0.9360   0.0889
  -1.500   0.2844   0.02952   0.02471  -0.1096   0.9320   0.0914
  -1.250   0.3341   0.02740   0.02212  -0.1138   0.9292   0.1018
  -1.000   0.3685   0.02510   0.01991  -0.1162   0.9261   0.1053
  -0.750   0.4076   0.02339   0.01795  -0.1185   0.9198   0.1173
  -0.500   0.4520   0.02173   0.01609  -0.1221   0.9159   0.1307
  -0.250   0.5009   0.02016   0.01446  -0.1270   0.9123   0.1482
   0.000   0.2553   0.01655   0.01279  -0.0537   0.9023   0.1463
   0.250   0.5876   0.01811   0.01215  -0.1341   0.8935   0.2047
   0.750   0.6617   0.01598   0.00933  -0.1362   0.8712   0.1604
   1.000   0.6967   0.01542   0.00856  -0.1372   0.8609   0.1530
   1.250   0.7247   0.01497   0.00800  -0.1369   0.8491   0.1503
   1.500   0.7522   0.01474   0.00769  -0.1364   0.8375   0.1519
   1.750   0.7810   0.01450   0.00737  -0.1361   0.8254   0.1529
   2.000   0.8078   0.01424   0.00703  -0.1353   0.8096   0.1530
   2.250   0.8327   0.01402   0.00675  -0.1340   0.7916   0.1539
   2.500   0.8574   0.01385   0.00652  -0.1327   0.7732   0.1555
   2.750   0.8820   0.01361   0.00627  -0.1314   0.7528   0.1585
   3.000   0.9073   0.01340   0.00608  -0.1304   0.7323   0.1608
   3.250   0.9320   0.01327   0.00593  -0.1292   0.7079   0.1632
   3.500   0.9559   0.01320   0.00584  -0.1277   0.6794   0.1657
   3.750   0.9793   0.01321   0.00578  -0.1263   0.6426   0.1688
   4.000   1.0005   0.01340   0.00576  -0.1243   0.5835   0.1722
   4.250   1.0159   0.01405   0.00588  -0.1213   0.4663   0.1772
   4.500   1.0181   0.01602   0.00664  -0.1163   0.2574   0.1812
   4.750   1.0254   0.01829   0.00784  -0.1128   0.0912   0.1853
   5.000   1.0504   0.01903   0.00862  -0.1124   0.0786   0.1916
   5.250   1.0722   0.02004   0.00964  -0.1112   0.0719   0.2008
   5.500   1.0980   0.02074   0.01045  -0.1109   0.0677   0.2165
   5.750   1.1829   0.02274   0.01342  -0.1254   0.0593   1.0000
   6.000   1.2046   0.02365   0.01433  -0.1239   0.0578   1.0000
   6.250   1.2264   0.02468   0.01537  -0.1225   0.0559   1.0000
   6.500   1.2486   0.02575   0.01645  -0.1213   0.0537   1.0000
   6.750   1.2709   0.02690   0.01762  -0.1202   0.0514   1.0000
   7.000   1.2945   0.02836   0.01907  -0.1194   0.0501   1.0000
   7.250   1.3199   0.03041   0.02111  -0.1190   0.0488   1.0000
   7.500   1.3483   0.03392   0.02472  -0.1192   0.0477   1.0000
   7.750   1.3679   0.03459   0.02564  -0.1173   0.0465   1.0000
   8.000   1.3896   0.03627   0.02755  -0.1159   0.0457   1.0000
   8.250   1.4107   0.03859   0.03013  -0.1145   0.0454   1.0000
   8.500   1.4299   0.04127   0.03310  -0.1128   0.0453   1.0000
   8.750   1.4467   0.04449   0.03666  -0.1108   0.0456   1.0000
   9.000   1.4604   0.04784   0.04035  -0.1084   0.0459   1.0000
   9.250   1.4707   0.05091   0.04377  -0.1056   0.0457   1.0000
  12.750   1.1578   0.15279   0.14945  -0.1053   0.0666   1.0000
  13.000   1.1526   0.15947   0.15611  -0.1088   0.0648   1.0000
  13.250   1.1534   0.16404   0.16068  -0.1103   0.0630   1.0000
  13.500   1.1592   0.16690   0.16354  -0.1101   0.0616   1.0000
  13.750   1.1689   0.16839   0.16504  -0.1081   0.0605   1.0000
  14.000   0.8812   0.16420   0.16102  -0.0889   0.0683   1.0000
  14.250   0.8765   0.16826   0.16508  -0.0908   0.0656   1.0000
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