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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 100,000
Max Cl/Cd: 55.48 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda3-il-100000.txt
Download as CSV file: xf-coanda3-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 3                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4251   0.09479   0.09009  -0.0243   1.0000   0.0838
  -8.250  -0.4374   0.09290   0.08831  -0.0246   1.0000   0.0848
  -8.000  -0.4508   0.09116   0.08665  -0.0261   1.0000   0.0856
  -7.750  -0.3794   0.07554   0.07142  -0.0249   1.0000   0.0888
  -7.500  -0.3828   0.07253   0.06846  -0.0228   1.0000   0.0903
  -7.250  -0.3902   0.06964   0.06562  -0.0217   1.0000   0.0912
  -7.000  -0.4549   0.07729   0.07293  -0.0242   1.0000   0.0890
  -6.750  -0.4521   0.07432   0.06998  -0.0228   1.0000   0.0905
  -6.500  -0.4498   0.07112   0.06678  -0.0223   1.0000   0.0919
  -6.250  -0.4460   0.06794   0.06356  -0.0222   1.0000   0.0934
  -6.000  -0.4407   0.06443   0.05999  -0.0223   1.0000   0.0945
  -5.750  -0.4335   0.06079   0.05626  -0.0224   1.0000   0.0950
  -5.500  -0.4222   0.04975   0.04446  -0.0264   1.0000   0.0612
  -5.250  -0.4125   0.04692   0.04169  -0.0244   1.0000   0.0579
  -5.000  -0.4020   0.03769   0.03162  -0.0233   1.0000   0.0491
  -4.750  -0.3888   0.03410   0.02773  -0.0216   1.0000   0.0480
  -4.500  -0.3735   0.03005   0.02317  -0.0196   1.0000   0.0469
  -4.250  -0.3549   0.02576   0.01814  -0.0176   1.0000   0.0463
  -4.000  -0.3329   0.02265   0.01438  -0.0159   1.0000   0.0470
  -3.750  -0.3100   0.02063   0.01191  -0.0143   1.0000   0.0492
  -3.500  -0.2889   0.02004   0.01133  -0.0129   1.0000   0.0537
  -3.250  -0.2679   0.02003   0.01123  -0.0113   1.0000   0.0680
  -3.000  -0.2480   0.02019   0.01125  -0.0096   1.0000   0.0936
  -2.750  -0.2292   0.02058   0.01131  -0.0080   1.0000   0.1135
  -2.500  -0.2103   0.02054   0.01122  -0.0067   1.0000   0.1235
  -2.250  -0.1910   0.02049   0.01101  -0.0055   1.0000   0.1306
  -2.000  -0.1736   0.02066   0.01115  -0.0042   1.0000   0.1442
  -1.750  -0.1559   0.02074   0.01115  -0.0031   1.0000   0.1571
  -1.500  -0.1365   0.02055   0.01091  -0.0020   1.0000   0.1613
  -1.250  -0.1181   0.02050   0.01082  -0.0010   1.0000   0.1718
  -1.000  -0.0999   0.02048   0.01077   0.0000   1.0000   0.1839
  -0.750  -0.0666   0.02039   0.01068  -0.0017   0.9959   0.1877
  -0.500  -0.0145   0.02045   0.01067  -0.0068   0.9849   0.1927
  -0.250   0.0363   0.02032   0.01060  -0.0116   0.9730   0.1995
   0.000   0.0857   0.02017   0.01050  -0.0160   0.9608   0.2105
   0.250   0.1336   0.01997   0.01043  -0.0202   0.9505   0.2308
   0.500   0.2532   0.01795   0.01053  -0.0393   0.9550   1.0000
   0.750   0.2991   0.01808   0.01050  -0.0430   0.9440   1.0000
   1.000   0.3425   0.01810   0.01045  -0.0461   0.9320   1.0000
   1.250   0.3876   0.01802   0.01036  -0.0494   0.9195   1.0000
   1.500   0.4375   0.01771   0.01009  -0.0534   0.9061   1.0000
   1.750   0.4927   0.01710   0.00958  -0.0579   0.8917   1.0000
   2.000   0.5478   0.01637   0.00897  -0.0622   0.8774   1.0000
   2.250   0.5976   0.01562   0.00835  -0.0654   0.8615   1.0000
   2.500   0.6309   0.01511   0.00801  -0.0654   0.8382   1.0000
   2.750   0.6667   0.01452   0.00755  -0.0657   0.8103   1.0000
   3.000   0.7030   0.01398   0.00709  -0.0659   0.7714   1.0000
   3.250   0.7420   0.01362   0.00666  -0.0666   0.7127   1.0000
   3.500   0.7679   0.01384   0.00667  -0.0650   0.6334   1.0000
   3.750   0.7830   0.01439   0.00675  -0.0617   0.5379   1.0000
   4.000   0.7945   0.01516   0.00695  -0.0581   0.4536   1.0000
   4.250   0.8098   0.01591   0.00739  -0.0556   0.4028   1.0000
   4.500   0.8270   0.01659   0.00791  -0.0535   0.3671   1.0000
   4.750   0.8414   0.01722   0.00837  -0.0510   0.3194   1.0000
   5.000   0.8583   0.01773   0.00888  -0.0489   0.2810   1.0000
   5.250   0.8755   0.01822   0.00929  -0.0467   0.2292   1.0000
   5.500   0.8881   0.01941   0.00983  -0.0440   0.1172   1.0000
   5.750   0.8983   0.02133   0.01112  -0.0410   0.0537   1.0000
   6.000   0.9133   0.02261   0.01241  -0.0386   0.0457   1.0000
   6.250   0.9286   0.02372   0.01372  -0.0360   0.0429   1.0000
   6.500   0.9416   0.02496   0.01514  -0.0332   0.0411   1.0000
   6.750   0.9535   0.02634   0.01665  -0.0302   0.0400   1.0000
   7.000   0.9669   0.02785   0.01825  -0.0276   0.0395   1.0000
   7.250   0.9848   0.02969   0.02024  -0.0256   0.0393   1.0000
   7.500   1.0092   0.03201   0.02271  -0.0245   0.0396   1.0000
   7.750   1.0323   0.03459   0.02544  -0.0236   0.0386   1.0000
   8.000   1.0535   0.03750   0.02856  -0.0224   0.0378   1.0000
   8.250   1.0705   0.04045   0.03185  -0.0206   0.0377   1.0000
   8.500   1.0811   0.04335   0.03539  -0.0172   0.0399   1.0000
   8.750   1.0834   0.04711   0.03977  -0.0134   0.0424   1.0000
   9.000   1.0837   0.05125   0.04431  -0.0100   0.0446   1.0000
   9.250   1.0849   0.05631   0.04959  -0.0076   0.0465   1.0000
   9.500   1.0755   0.05860   0.05247  -0.0026   0.0497   1.0000
   9.750   1.0485   0.06226   0.05658   0.0027   0.0515   1.0000
  10.000   1.0219   0.06612   0.06070   0.0069   0.0528   1.0000
  10.250   0.9995   0.06996   0.06473   0.0091   0.0536   1.0000
  10.500   0.9752   0.07436   0.06930   0.0098   0.0540   1.0000
  10.750   0.9498   0.07946   0.07454   0.0085   0.0539   1.0000
  11.000   0.9220   0.08598   0.08118   0.0048   0.0533   1.0000
  11.250   0.8957   0.09418   0.08945  -0.0012   0.0526   1.0000
  11.500   0.8671   0.10603   0.10129  -0.0096   0.0526   1.0000
  11.750   0.8481   0.11639   0.11158  -0.0151   0.0552   1.0000
  12.000   0.7145   0.11606   0.11153  -0.0095   0.0558   1.0000
  12.250   0.7124   0.12023   0.11570  -0.0100   0.0576   1.0000
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