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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 100,000
Max Cl/Cd: 52.71 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe611-il-100000.txt
Download as CSV file: xf-goe611-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 611 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3201   0.12357   0.11939  -0.0313   1.0000   0.0553
  -9.000  -0.3381   0.12329   0.11920  -0.0296   1.0000   0.0555
  -8.750  -0.3563   0.12287   0.11887  -0.0279   1.0000   0.0556
  -8.500  -0.3633   0.12116   0.11721  -0.0320   0.9958   0.0559
  -8.250  -0.3377   0.11351   0.10956  -0.0326   0.9937   0.0571
  -8.000  -0.3105   0.10850   0.10452  -0.0331   0.9902   0.0599
  -7.750  -0.2940   0.10463   0.10064  -0.0376   0.9848   0.0631
  -7.500  -0.2874   0.10140   0.09743  -0.0422   0.9763   0.0659
  -7.250  -0.2771   0.09781   0.09379  -0.0566   0.9635   0.0686
  -7.000  -0.2606   0.09239   0.08828  -0.0665   0.9550   0.0698
  -6.750  -0.2444   0.08802   0.08400  -0.0610   0.9510   0.0723
  -6.500  -0.2203   0.08394   0.07989  -0.0649   0.9455   0.0762
  -6.250  -0.2041   0.08020   0.07607  -0.0709   0.9353   0.0811
  -6.000  -0.1726   0.07433   0.06997  -0.0822   0.9293   0.0855
  -5.750  -0.1627   0.07151   0.06723  -0.0800   0.9199   0.0884
  -5.500  -0.1297   0.06954   0.06463  -0.0900   0.9097   0.0994
  -5.250  -0.1126   0.06374   0.05918  -0.0887   0.9047   0.1031
  -5.000  -0.0742   0.05954   0.05474  -0.0952   0.9006   0.1176
  -4.750  -0.0546   0.05755   0.05245  -0.0970   0.8896   0.1318
  -4.500  -0.0173   0.05336   0.04821  -0.1011   0.8863   0.1484
  -4.000   0.0391   0.04787   0.04252  -0.1049   0.8724   0.1960
  -2.500   0.2337   0.03312   0.02673  -0.1137   0.8302   0.2945
  -2.250   0.3094   0.02990   0.02143  -0.1165   0.8267   0.1123
  -2.000   0.3363   0.02869   0.02000  -0.1158   0.8169   0.1085
  -1.750   0.3755   0.02718   0.01817  -0.1168   0.8115   0.1050
  -1.500   0.4026   0.02657   0.01731  -0.1158   0.8014   0.1014
  -1.250   0.4396   0.02553   0.01609  -0.1164   0.7957   0.1002
  -1.000   0.4634   0.02491   0.01550  -0.1155   0.7851   0.1020
  -0.750   0.4985   0.02388   0.01449  -0.1160   0.7795   0.1065
  -0.500   0.5201   0.02367   0.01428  -0.1147   0.7684   0.1084
  -0.250   0.5552   0.02290   0.01340  -0.1151   0.7632   0.1124
   0.000   0.5766   0.02286   0.01333  -0.1138   0.7517   0.1176
   0.250   0.6033   0.02266   0.01308  -0.1133   0.7429   0.1322
   0.500   0.6419   0.02008   0.01277  -0.1144   0.7357   1.0000
   0.750   0.6661   0.02034   0.01272  -0.1134   0.7261   1.0000
   1.000   0.6974   0.02022   0.01231  -0.1134   0.7192   1.0000
   1.250   0.7193   0.02056   0.01251  -0.1124   0.7087   1.0000
   1.500   0.7527   0.02035   0.01208  -0.1128   0.7029   1.0000
   1.750   0.7732   0.02076   0.01241  -0.1117   0.6920   1.0000
   2.000   0.8002   0.02088   0.01241  -0.1114   0.6840   1.0000
   2.250   0.8275   0.02097   0.01239  -0.1111   0.6756   1.0000
   2.500   0.8515   0.02124   0.01259  -0.1105   0.6662   1.0000
   2.750   0.8834   0.02106   0.01227  -0.1108   0.6589   1.0000
   3.000   0.9053   0.02138   0.01256  -0.1098   0.6482   1.0000
   3.250   0.9332   0.02138   0.01247  -0.1095   0.6391   1.0000
   3.500   0.9618   0.02134   0.01234  -0.1094   0.6299   1.0000
   3.750   0.9847   0.02161   0.01258  -0.1085   0.6192   1.0000
   4.000   1.0138   0.02162   0.01249  -0.1085   0.6107   1.0000
   4.250   1.0388   0.02184   0.01270  -0.1080   0.6010   1.0000
   4.500   1.0624   0.02213   0.01299  -0.1073   0.5912   1.0000
   4.750   1.0941   0.02208   0.01280  -0.1078   0.5831   1.0000
   5.000   1.1141   0.02252   0.01330  -0.1066   0.5723   1.0000
   5.250   1.1391   0.02281   0.01360  -0.1061   0.5634   1.0000
   5.500   1.1661   0.02304   0.01380  -0.1060   0.5549   1.0000
   5.750   1.1874   0.02353   0.01436  -0.1051   0.5457   1.0000
   6.000   1.2177   0.02367   0.01444  -0.1055   0.5383   1.0000
   6.250   1.2359   0.02425   0.01515  -0.1041   0.5283   1.0000
   6.500   1.2624   0.02452   0.01541  -0.1039   0.5200   1.0000
   6.750   1.2848   0.02488   0.01582  -0.1031   0.5105   1.0000
   7.000   1.3058   0.02536   0.01640  -0.1022   0.5014   1.0000
   7.250   1.3339   0.02556   0.01658  -0.1023   0.4934   1.0000
   7.500   1.3504   0.02611   0.01728  -0.1006   0.4831   1.0000
   7.750   1.3740   0.02637   0.01759  -0.0999   0.4737   1.0000
   8.000   1.3966   0.02666   0.01793  -0.0991   0.4642   1.0000
   8.250   1.4131   0.02720   0.01862  -0.0975   0.4545   1.0000
   8.500   1.4380   0.02742   0.01885  -0.0970   0.4454   1.0000
   8.750   1.4555   0.02764   0.01917  -0.0953   0.4336   1.0000
   9.000   1.4680   0.02785   0.01947  -0.0928   0.4200   1.0000
   9.250   1.4788   0.02806   0.01975  -0.0900   0.4057   1.0000
   9.500   1.4871   0.02838   0.02014  -0.0868   0.3914   1.0000
   9.750   1.4926   0.02881   0.02064  -0.0833   0.3771   1.0000
  10.000   1.4926   0.02935   0.02126  -0.0790   0.3628   1.0000
  10.250   1.4925   0.03011   0.02207  -0.0750   0.3481   1.0000
  10.500   1.4928   0.03105   0.02308  -0.0713   0.3334   1.0000
  10.750   1.4927   0.03220   0.02428  -0.0680   0.3182   1.0000
  11.000   1.4913   0.03357   0.02568  -0.0649   0.3024   1.0000
  11.250   1.4887   0.03519   0.02730  -0.0619   0.2862   1.0000
  11.500   1.4842   0.03711   0.02922  -0.0592   0.2695   1.0000
  11.750   1.4785   0.03934   0.03149  -0.0568   0.2526   1.0000
  12.000   1.4743   0.04165   0.03381  -0.0547   0.2381   1.0000
  12.250   1.4716   0.04399   0.03614  -0.0530   0.2262   1.0000
  12.500   1.4689   0.04643   0.03863  -0.0514   0.2154   1.0000
  12.750   1.4668   0.04897   0.04125  -0.0501   0.2052   1.0000
  13.000   1.4639   0.05164   0.04398  -0.0490   0.1963   1.0000
  13.250   1.4570   0.05480   0.04714  -0.0480   0.1865   1.0000
  13.500   1.4519   0.05804   0.05050  -0.0473   0.1768   1.0000
  13.750   1.4473   0.06131   0.05385  -0.0468   0.1689   1.0000
  14.000   1.4428   0.06466   0.05730  -0.0464   0.1621   1.0000
  14.250   1.4361   0.06845   0.06120  -0.0464   0.1540   1.0000
  14.500   1.4281   0.07245   0.06523  -0.0464   0.1472   1.0000
  14.750   1.4201   0.07671   0.06962  -0.0467   0.1391   1.0000
  15.000   1.4089   0.08137   0.07430  -0.0472   0.1315   1.0000
  15.250   1.3975   0.08630   0.07933  -0.0479   0.1231   1.0000
  15.500   1.3868   0.09127   0.08442  -0.0488   0.1148   1.0000
  15.750   1.3723   0.09685   0.09001  -0.0500   0.1064   1.0000
  16.000   1.3617   0.10224   0.09563  -0.0515   0.0946   1.0000
  16.250   1.3500   0.10788   0.10135  -0.0531   0.0650   1.0000
  16.500   1.3308   0.11458   0.10788  -0.0553   0.0564   1.0000
  16.750   1.3159   0.12066   0.11391  -0.0573   0.0512   1.0000
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