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GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 481A AIRFOIL (goe481a-il)
Reynolds number: 200,000
Max Cl/Cd: 63.81 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe481a-il-200000.txt
Download as CSV file: xf-goe481a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481A 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1628   0.09941   0.09570  -0.0596   0.9529   0.0941
  -7.000  -0.1450   0.09639   0.09267  -0.0625   0.9480   0.0958
  -6.750  -0.2023   0.09038   0.08663  -0.0766   0.9323   0.1006
  -6.500  -0.1825   0.08779   0.08408  -0.0738   0.9271   0.1009
  -6.250  -0.1566   0.08545   0.08175  -0.0724   0.9228   0.1016
  -6.000  -0.1285   0.08269   0.07900  -0.0739   0.9196   0.1027
  -5.750  -0.1089   0.07976   0.07606  -0.0762   0.9144   0.1044
  -5.500  -0.1158   0.07107   0.06717  -0.0899   0.9020   0.1106
  -5.250  -0.1071   0.06928   0.06543  -0.0867   0.8915   0.1111
  -5.000  -0.0777   0.06691   0.06308  -0.0874   0.8885   0.1122
  -4.750  -0.0468   0.06375   0.05989  -0.0906   0.8860   0.1142
  -4.500  -0.0405   0.06094   0.05703  -0.0904   0.8735   0.1168
  -4.250  -0.0168   0.05401   0.04978  -0.0984   0.8694   0.1218
  -4.000  -0.0503   0.03689   0.03140  -0.0972   0.8548   0.0925
  -3.750  -0.0236   0.03238   0.02645  -0.0980   0.8524   0.0907
  -3.500  -0.0155   0.02989   0.02364  -0.0946   0.8400   0.0905
  -3.250   0.0117   0.02643   0.01957  -0.0945   0.8369   0.0913
  -3.000   0.0493   0.02457   0.01754  -0.0959   0.8348   0.0930
  -2.750   0.0670   0.02389   0.01684  -0.0935   0.8221   0.0941
  -2.500   0.1070   0.02253   0.01536  -0.0952   0.8184   0.0958
  -2.250   0.1307   0.02138   0.01403  -0.0938   0.8069   0.0972
  -2.000   0.1709   0.01987   0.01219  -0.0955   0.8006   0.1000
  -1.750   0.2025   0.01912   0.01143  -0.0957   0.7884   0.1024
  -1.500   0.2533   0.01824   0.01049  -0.0996   0.7803   0.1061
  -1.250   0.2879   0.01749   0.00951  -0.1004   0.7653   0.1099
  -1.000   0.3295   0.01693   0.00897  -0.1028   0.7504   0.1136
  -0.750   0.3721   0.01650   0.00833  -0.1052   0.7348   0.1201
  -0.500   0.4133   0.01619   0.00799  -0.1076   0.7189   0.1259
  -0.250   0.4519   0.01594   0.00757  -0.1095   0.7033   0.1345
   0.000   0.4778   0.01594   0.00746  -0.1088   0.6877   0.1433
   0.250   0.5046   0.01582   0.00732  -0.1084   0.6735   0.1529
   0.500   0.5361   0.01571   0.00712  -0.1090   0.6605   0.1644
   0.750   0.5586   0.01581   0.00709  -0.1076   0.6476   0.1739
   1.000   0.5836   0.01566   0.00698  -0.1070   0.6361   0.1830
   1.250   0.6113   0.01569   0.00689  -0.1068   0.6254   0.1916
   1.500   0.6325   0.01565   0.00690  -0.1053   0.6150   0.1993
   1.750   0.6596   0.01574   0.00689  -0.1050   0.6050   0.2073
   2.000   0.6790   0.01571   0.00692  -0.1032   0.5949   0.2150
   2.250   0.7031   0.01581   0.00696  -0.1022   0.5851   0.2246
   2.500   0.7225   0.01583   0.00702  -0.1004   0.5755   0.2329
   2.750   0.7430   0.01589   0.00707  -0.0987   0.5660   0.2406
   3.000   0.7646   0.01600   0.00714  -0.0973   0.5567   0.2481
   3.250   0.7807   0.01602   0.00723  -0.0947   0.5475   0.2570
   3.500   0.8064   0.01613   0.00730  -0.0942   0.5390   0.2699
   3.750   0.9750   0.01558   0.00834  -0.1249   0.5207   1.0000
   4.000   0.9837   0.01574   0.00850  -0.1208   0.5121   1.0000
   4.250   1.0034   0.01597   0.00859  -0.1190   0.5038   1.0000
   4.500   1.0211   0.01621   0.00877  -0.1168   0.4957   1.0000
   4.750   1.0362   0.01642   0.00893  -0.1141   0.4876   1.0000
   5.000   1.0604   0.01671   0.00907  -0.1133   0.4798   1.0000
   5.250   1.0715   0.01691   0.00930  -0.1098   0.4718   1.0000
   5.500   1.0904   0.01715   0.00945  -0.1080   0.4644   1.0000
   5.750   1.1096   0.01743   0.00969  -0.1062   0.4573   1.0000
   6.000   1.1245   0.01768   0.00994  -0.1036   0.4500   1.0000
   6.250   1.1461   0.01796   0.01012  -0.1024   0.4433   1.0000
   6.500   1.1628   0.01825   0.01042  -0.1002   0.4366   1.0000
   6.750   1.1779   0.01852   0.01069  -0.0977   0.4295   1.0000
   7.000   1.2003   0.01883   0.01087  -0.0966   0.4230   1.0000
   7.250   1.2132   0.01913   0.01124  -0.0938   0.4161   1.0000
   7.500   1.2285   0.01943   0.01154  -0.0915   0.4094   1.0000
   7.750   1.2522   0.01978   0.01175  -0.0907   0.4030   1.0000
   8.000   1.2628   0.02011   0.01219  -0.0876   0.3964   1.0000
   8.250   1.2777   0.02045   0.01253  -0.0852   0.3897   1.0000
   8.500   1.2969   0.02082   0.01281  -0.0838   0.3829   1.0000
   8.750   1.3065   0.02121   0.01328  -0.0806   0.3755   1.0000
   9.000   1.3209   0.02159   0.01360  -0.0782   0.3681   1.0000
   9.250   1.3330   0.02204   0.01409  -0.0756   0.3605   1.0000
   9.500   1.3436   0.02249   0.01456  -0.0728   0.3527   1.0000
   9.750   1.3588   0.02299   0.01498  -0.0708   0.3453   1.0000
  10.000   1.3665   0.02353   0.01561  -0.0677   0.3370   1.0000
  10.250   1.3801   0.02408   0.01605  -0.0655   0.3289   1.0000
  10.500   1.3865   0.02473   0.01682  -0.0623   0.3205   1.0000
  10.750   1.3962   0.02540   0.01741  -0.0598   0.3119   1.0000
  11.000   1.4028   0.02616   0.01826  -0.0568   0.3029   1.0000
  11.250   1.4117   0.02694   0.01898  -0.0543   0.2946   1.0000
  11.500   1.4183   0.02783   0.01994  -0.0516   0.2857   1.0000
  11.750   1.4249   0.02876   0.02081  -0.0490   0.2772   1.0000
  12.000   1.4310   0.02976   0.02188  -0.0465   0.2686   1.0000
  12.250   1.4374   0.03080   0.02288  -0.0441   0.2610   1.0000
  12.500   1.4445   0.03190   0.02401  -0.0419   0.2539   1.0000
  12.750   1.4509   0.03304   0.02519  -0.0397   0.2469   1.0000
  13.000   1.4583   0.03421   0.02629  -0.0377   0.2412   1.0000
  13.250   1.4645   0.03548   0.02767  -0.0358   0.2349   1.0000
  13.500   1.4709   0.03677   0.02895  -0.0340   0.2296   1.0000
  13.750   1.4784   0.03805   0.03021  -0.0323   0.2247   1.0000
  14.000   1.4841   0.03949   0.03177  -0.0306   0.2197   1.0000
  14.250   1.4890   0.04100   0.03330  -0.0290   0.2148   1.0000
  14.500   1.4973   0.04231   0.03451  -0.0276   0.2102   1.0000
  14.750   1.5001   0.04410   0.03646  -0.0262   0.2057   1.0000
  15.000   1.5031   0.04592   0.03834  -0.0248   0.2010   1.0000
  15.250   1.5089   0.04750   0.03987  -0.0236   0.1965   1.0000
  15.500   1.5118   0.04943   0.04188  -0.0224   0.1921   1.0000
  15.750   1.5125   0.05160   0.04416  -0.0213   0.1875   1.0000
  16.000   1.5158   0.05352   0.04605  -0.0203   0.1829   1.0000
  16.250   1.5195   0.05547   0.04803  -0.0193   0.1783   1.0000
  16.500   1.5167   0.05816   0.05085  -0.0186   0.1736   1.0000
  16.750   1.5183   0.06035   0.05303  -0.0178   0.1690   1.0000
  17.000   1.5210   0.06247   0.05515  -0.0170   0.1641   1.0000
  17.250   1.5158   0.06560   0.05841  -0.0166   0.1595   1.0000
  17.500   1.5175   0.06787   0.06067  -0.0161   0.1550   1.0000
  17.750   1.5172   0.07043   0.06325  -0.0156   0.1503   1.0000
  18.000   1.5113   0.07377   0.06673  -0.0155   0.1463   1.0000
  18.250   1.5114   0.07638   0.06935  -0.0154   0.1425   1.0000
  18.500   1.5182   0.07808   0.07099  -0.0149   0.1387   1.0000
  18.750   1.5071   0.08228   0.07540  -0.0154   0.1355   1.0000
  19.000   1.5038   0.08547   0.07868  -0.0157   0.1324   1.0000
  19.250   1.5058   0.08791   0.08112  -0.0158   0.1296   1.0000
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