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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 200,000
Max Cl/Cd: 86.53 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610b-il-200000.txt
Download as CSV file: xf-goe610b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2972   0.09852   0.09521  -0.0344   1.0000   0.0375
  -8.000  -0.3166   0.09846   0.09528  -0.0313   1.0000   0.0376
  -7.750  -0.3411   0.09903   0.09596  -0.0283   0.9984   0.0377
  -7.500  -0.3084   0.09419   0.09107  -0.0437   0.9889   0.0380
  -7.250  -0.2943   0.08780   0.08470  -0.0438   0.9859   0.0386
  -7.000  -0.2744   0.08336   0.08025  -0.0437   0.9837   0.0394
  -6.750  -0.2532   0.07949   0.07636  -0.0475   0.9768   0.0403
  -6.500  -0.2256   0.07523   0.07207  -0.0540   0.9716   0.0420
  -6.250  -0.1990   0.07104   0.06784  -0.0610   0.9634   0.0445
  -6.000  -0.1347   0.06570   0.06213  -0.0834   0.9562   0.0471
  -5.750  -0.1262   0.06027   0.05679  -0.0824   0.9490   0.0481
  -5.500  -0.1015   0.05674   0.05326  -0.0842   0.9450   0.0494
  -5.250  -0.0677   0.05306   0.04950  -0.0892   0.9415   0.0520
  -4.750  -0.0007   0.04475   0.04080  -0.1001   0.9262   0.0598
  -4.500   0.0209   0.04243   0.03842  -0.1006   0.9167   0.0624
  -4.250   0.0579   0.03887   0.03436  -0.1049   0.9082   0.0708
  -4.000   0.0788   0.03660   0.03219  -0.1050   0.9000   0.0736
  -3.750   0.1079   0.03442   0.02960  -0.1063   0.8898   0.0839
  -3.500   0.1313   0.03226   0.02746  -0.1065   0.8817   0.0870
  -3.250   0.1577   0.03060   0.02540  -0.1066   0.8704   0.0977
  -3.000   0.1783   0.02892   0.02377  -0.1060   0.8595   0.1026
  -2.750   0.2041   0.02729   0.02184  -0.1059   0.8496   0.1132
  -2.500   0.2299   0.02630   0.02051  -0.1054   0.8390   0.1257
  -2.250   0.2510   0.02459   0.01882  -0.1047   0.8273   0.1303
  -2.000   0.2749   0.02343   0.01747  -0.1041   0.8164   0.1433
  -1.750   0.2999   0.02233   0.01616  -0.1036   0.8068   0.1574
  -1.500   0.3233   0.02134   0.01503  -0.1028   0.7953   0.1718
  -1.250   0.3591   0.01843   0.01109  -0.1011   0.7859   0.0938
  -1.000   0.3859   0.01737   0.00980  -0.1005   0.7768   0.0923
  -0.750   0.4115   0.01631   0.00852  -0.0996   0.7654   0.0887
  -0.500   0.4376   0.01549   0.00748  -0.0987   0.7543   0.0867
  -0.250   0.4642   0.01488   0.00672  -0.0981   0.7448   0.0865
   0.000   0.4904   0.01441   0.00617  -0.0975   0.7351   0.0875
   0.250   0.5162   0.01412   0.00585  -0.0969   0.7256   0.0906
   0.500   0.5431   0.01376   0.00540  -0.0964   0.7178   0.0925
   0.750   0.5681   0.01344   0.00509  -0.0956   0.7077   0.0940
   1.000   0.5940   0.01321   0.00482  -0.0950   0.6998   0.0959
   1.250   0.6190   0.01288   0.00453  -0.0943   0.6912   0.0994
   1.500   0.6440   0.01273   0.00440  -0.0936   0.6821   0.1045
   1.750   0.6699   0.01260   0.00424  -0.0930   0.6744   0.1137
   2.000   0.6946   0.01249   0.00420  -0.0923   0.6661   0.1315
   2.250   0.7718   0.01069   0.00410  -0.1033   0.6578   1.0000
   2.500   0.7965   0.01083   0.00420  -0.1025   0.6503   1.0000
   2.750   0.8220   0.01099   0.00425  -0.1019   0.6435   1.0000
   3.000   0.8462   0.01114   0.00438  -0.1011   0.6354   1.0000
   3.250   0.8714   0.01130   0.00449  -0.1004   0.6281   1.0000
   3.500   0.8955   0.01146   0.00465  -0.0996   0.6198   1.0000
   3.750   0.9204   0.01164   0.00479  -0.0989   0.6126   1.0000
   4.000   0.9444   0.01180   0.00497  -0.0981   0.6042   1.0000
   4.250   0.9687   0.01199   0.00516  -0.0973   0.5962   1.0000
   4.500   0.9926   0.01215   0.00533  -0.0964   0.5867   1.0000
   4.750   1.0159   0.01233   0.00555  -0.0954   0.5773   1.0000
   5.000   1.0397   0.01251   0.00573  -0.0945   0.5677   1.0000
   5.250   1.0625   0.01267   0.00594  -0.0934   0.5563   1.0000
   5.500   1.0847   0.01283   0.00617  -0.0922   0.5439   1.0000
   5.750   1.1068   0.01300   0.00639  -0.0910   0.5309   1.0000
   6.000   1.1282   0.01316   0.00660  -0.0896   0.5153   1.0000
   6.250   1.1486   0.01333   0.00680  -0.0880   0.4964   1.0000
   6.500   1.1673   0.01349   0.00700  -0.0861   0.4696   1.0000
   6.750   1.1845   0.01371   0.00719  -0.0840   0.4326   1.0000
   7.000   1.1971   0.01419   0.00741  -0.0811   0.3807   1.0000
   7.250   1.2071   0.01499   0.00792  -0.0780   0.3418   1.0000
   7.500   1.2187   0.01581   0.00858  -0.0753   0.3128   1.0000
   7.750   1.2324   0.01654   0.00921  -0.0730   0.2908   1.0000
   8.000   1.2475   0.01714   0.00981  -0.0709   0.2669   1.0000
   8.250   1.2605   0.01780   0.01042  -0.0685   0.2366   1.0000
   8.500   1.2692   0.01866   0.01110  -0.0656   0.1873   1.0000
   8.750   1.2656   0.02014   0.01213  -0.0608   0.1318   1.0000
   9.000   1.2613   0.02173   0.01358  -0.0560   0.0996   1.0000
   9.250   1.2569   0.02350   0.01495  -0.0515   0.0578   1.0000
   9.500   1.2545   0.02517   0.01661  -0.0476   0.0486   1.0000
   9.750   1.2565   0.02668   0.01821  -0.0445   0.0434   1.0000
  10.000   1.2586   0.02826   0.01987  -0.0417   0.0402   1.0000
  10.250   1.2554   0.03038   0.02203  -0.0388   0.0379   1.0000
  10.500   1.2574   0.03225   0.02399  -0.0364   0.0362   1.0000
  10.750   1.2635   0.03386   0.02572  -0.0346   0.0343   1.0000
  11.000   1.2690   0.03557   0.02752  -0.0328   0.0326   1.0000
  11.250   1.2736   0.03745   0.02944  -0.0311   0.0310   1.0000
  11.500   1.2784   0.03950   0.03151  -0.0294   0.0298   1.0000
  11.750   1.2899   0.04173   0.03376  -0.0275   0.0286   1.0000
  12.000   1.3027   0.04342   0.03561  -0.0261   0.0279   1.0000
  12.250   1.3170   0.04530   0.03765  -0.0247   0.0272   1.0000
  12.500   1.3285   0.04729   0.03981  -0.0235   0.0265   1.0000
  12.750   1.3372   0.04943   0.04215  -0.0222   0.0256   1.0000
  13.000   1.3448   0.05173   0.04462  -0.0211   0.0248   1.0000
  13.250   1.3496   0.05413   0.04716  -0.0200   0.0240   1.0000
  13.500   1.3539   0.05702   0.05028  -0.0189   0.0239   1.0000
  13.750   1.3544   0.06029   0.05377  -0.0178   0.0237   1.0000
  14.000   1.3512   0.06383   0.05755  -0.0169   0.0235   1.0000
  14.250   1.3443   0.06781   0.06180  -0.0163   0.0236   1.0000
  14.500   1.3321   0.07238   0.06666  -0.0160   0.0238   1.0000
  14.750   1.3147   0.07747   0.07204  -0.0164   0.0239   1.0000
  15.000   1.2929   0.08336   0.07824  -0.0174   0.0242   1.0000
  15.250   1.2683   0.09002   0.08520  -0.0194   0.0246   1.0000
  15.500   1.2432   0.09726   0.09271  -0.0222   0.0249   1.0000
  15.750   1.2185   0.10499   0.10067  -0.0258   0.0254   1.0000
  16.000   1.1932   0.11341   0.10930  -0.0303   0.0257   1.0000
  16.250   1.1682   0.12251   0.11859  -0.0357   0.0261   1.0000
  16.500   1.1408   0.13311   0.12936  -0.0425   0.0265   1.0000
  16.750   1.1127   0.14513   0.14152  -0.0504   0.0270   1.0000
  17.000   1.0826   0.15907   0.15552  -0.0593   0.0278   1.0000
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