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GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 405 AIRFOIL (goe405-il)
Reynolds number: 100,000
Max Cl/Cd: 54.29 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe405-il-100000.txt
Download as CSV file: xf-goe405-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 405 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2641   0.11299   0.10886  -0.0405   0.9794   0.0853
  -7.750  -0.2702   0.11280   0.10871  -0.0486   0.9708   0.0874
  -7.500  -0.2784   0.11204   0.10799  -0.0566   0.9585   0.0879
  -7.250  -0.2381   0.10340   0.09931  -0.0506   0.9599   0.0907
  -7.000  -0.2224   0.10020   0.09610  -0.0525   0.9546   0.0942
  -6.750  -0.2221   0.09821   0.09413  -0.0541   0.9457   0.0979
  -6.500  -0.2269   0.09736   0.09326  -0.0663   0.9317   0.1014
  -6.250  -0.2079   0.09182   0.08775  -0.0634   0.9294   0.1038
  -6.000  -0.1963   0.08910   0.08501  -0.0622   0.9230   0.1074
  -5.750  -0.1820   0.08607   0.08194  -0.0672   0.9151   0.1131
  -5.500  -0.1753   0.08311   0.07888  -0.0761   0.9042   0.1167
  -5.250  -0.1562   0.07919   0.07499  -0.0738   0.9003   0.1193
  -5.000  -0.1437   0.07666   0.07244  -0.0742   0.8929   0.1238
  -4.750  -0.1170   0.07263   0.06825  -0.0829   0.8853   0.1323
  -4.500  -0.1046   0.07016   0.06579  -0.0809   0.8784   0.1367
  -4.250  -0.0711   0.06638   0.06175  -0.0896   0.8708   0.1467
  -4.000  -0.0512   0.06331   0.05868  -0.0891   0.8653   0.1503
  -3.750  -0.0233   0.06057   0.05566  -0.0941   0.8569   0.1619
  -3.500   0.0107   0.05723   0.05230  -0.0960   0.8537   0.1709
  -3.250   0.0509   0.04817   0.04207  -0.1050   0.8449   0.1158
  -3.000   0.0849   0.04473   0.03859  -0.1071   0.8407   0.1124
  -2.750   0.1349   0.03725   0.02982  -0.1122   0.8388   0.1023
  -2.500   0.1476   0.03600   0.02832  -0.1102   0.8291   0.1033
  -2.250   0.1895   0.03464   0.02682  -0.1125   0.8252   0.1093
  -2.000   0.2104   0.03352   0.02524  -0.1113   0.8169   0.1140
  -1.750   0.2484   0.03203   0.02349  -0.1128   0.8120   0.1203
  -1.500   0.2954   0.03077   0.02205  -0.1154   0.8093   0.1356
  -1.250   0.3089   0.03081   0.02201  -0.1131   0.7986   0.1487
  -1.000   0.3536   0.02993   0.02109  -0.1153   0.7954   0.1835
  -0.750   0.3701   0.03012   0.02121  -0.1134   0.7851   0.2089
  -0.500   0.4132   0.02938   0.02048  -0.1155   0.7815   0.2431
  -0.250   0.4344   0.02942   0.02043  -0.1144   0.7724   0.2665
   0.000   0.4759   0.02841   0.01943  -0.1162   0.7680   0.2880
   0.250   0.5283   0.02720   0.01814  -0.1198   0.7658   0.3114
   0.500   0.5454   0.02719   0.01818  -0.1179   0.7553   0.3247
   0.750   0.5937   0.02598   0.01706  -0.1207   0.7521   0.3505
   1.000   0.6454   0.02468   0.01586  -0.1241   0.7497   0.3884
   1.250   0.6869   0.02327   0.01596  -0.1269   0.7399   1.0000
   1.500   0.7347   0.02261   0.01495  -0.1294   0.7358   1.0000
   1.750   0.7545   0.02289   0.01509  -0.1278   0.7250   1.0000
   2.000   0.8003   0.02225   0.01424  -0.1301   0.7204   1.0000
   2.250   0.8190   0.02256   0.01447  -0.1283   0.7092   1.0000
   2.500   0.8656   0.02190   0.01366  -0.1309   0.7044   1.0000
   2.750   0.8826   0.02227   0.01398  -0.1288   0.6926   1.0000
   3.000   0.9089   0.02234   0.01398  -0.1283   0.6829   1.0000
   3.250   0.9460   0.02202   0.01357  -0.1294   0.6754   1.0000
   3.500   0.9653   0.02233   0.01386  -0.1277   0.6640   1.0000
   3.750   0.9983   0.02218   0.01363  -0.1282   0.6556   1.0000
   4.000   1.0257   0.02220   0.01361  -0.1279   0.6458   1.0000
   4.250   1.0455   0.02249   0.01390  -0.1263   0.6348   1.0000
   4.500   1.0787   0.02235   0.01368  -0.1269   0.6263   1.0000
   4.750   1.1027   0.02249   0.01381  -0.1260   0.6159   1.0000
   5.000   1.1224   0.02281   0.01418  -0.1245   0.6052   1.0000
   5.250   1.1549   0.02275   0.01405  -0.1251   0.5968   1.0000
   5.500   1.1761   0.02302   0.01435  -0.1238   0.5864   1.0000
   5.750   1.1960   0.02339   0.01477  -0.1224   0.5762   1.0000
   6.000   1.2303   0.02334   0.01466  -0.1233   0.5680   1.0000
   6.250   1.2464   0.02382   0.01522  -0.1213   0.5572   1.0000
   6.500   1.2674   0.02421   0.01566  -0.1201   0.5475   1.0000
   6.750   1.3017   0.02422   0.01563  -0.1211   0.5389   1.0000
   7.000   1.3143   0.02485   0.01638  -0.1186   0.5282   1.0000
   7.250   1.3366   0.02528   0.01687  -0.1177   0.5188   1.0000
   7.500   1.3668   0.02550   0.01710  -0.1180   0.5098   1.0000
   7.750   1.3796   0.02619   0.01793  -0.1156   0.4994   1.0000
   8.000   1.4033   0.02663   0.01842  -0.1149   0.4899   1.0000
   8.250   1.4310   0.02672   0.01848  -0.1147   0.4781   1.0000
   8.500   1.4505   0.02681   0.01854  -0.1130   0.4637   1.0000
   8.750   1.4657   0.02700   0.01876  -0.1106   0.4493   1.0000
   9.000   1.4751   0.02738   0.01923  -0.1074   0.4358   1.0000
   9.250   1.4835   0.02777   0.01971  -0.1041   0.4224   1.0000
   9.500   1.4888   0.02802   0.01998  -0.1002   0.4074   1.0000
   9.750   1.4863   0.02832   0.02030  -0.0950   0.3923   1.0000
  10.000   1.4824   0.02882   0.02088  -0.0899   0.3780   1.0000
  10.250   1.4777   0.02948   0.02163  -0.0850   0.3636   1.0000
  10.500   1.4714   0.03033   0.02257  -0.0803   0.3484   1.0000
  10.750   1.4625   0.03142   0.02371  -0.0755   0.3308   1.0000
  11.000   1.4476   0.03308   0.02542  -0.0707   0.3080   1.0000
  11.250   1.4311   0.03527   0.02756  -0.0664   0.2794   1.0000
  11.500   1.4121   0.03816   0.03028  -0.0626   0.2436   1.0000
  11.750   1.3932   0.04163   0.03352  -0.0595   0.2022   1.0000
  12.000   1.3704   0.04588   0.03745  -0.0570   0.1472   1.0000
  12.250   1.3427   0.05104   0.04220  -0.0550   0.0951   1.0000
  12.500   1.3207   0.05606   0.04703  -0.0536   0.0777   1.0000
  12.750   1.3045   0.06078   0.05176  -0.0527   0.0699   1.0000
  13.000   1.2901   0.06555   0.05661  -0.0523   0.0656   1.0000
  13.250   1.2758   0.07055   0.06171  -0.0522   0.0629   1.0000
  13.500   1.2656   0.07521   0.06657  -0.0524   0.0606   1.0000
  13.750   1.2544   0.08020   0.07171  -0.0528   0.0584   1.0000
  14.000   1.2441   0.08512   0.07678  -0.0534   0.0568   1.0000
  14.250   1.2331   0.09021   0.08197  -0.0542   0.0548   1.0000
  14.500   1.2251   0.09462   0.08642  -0.0545   0.0530   1.0000
  14.750   1.2271   0.09745   0.08933  -0.0543   0.0506   1.0000
  15.000   1.2367   0.09889   0.09085  -0.0532   0.0485   1.0000
  15.250   1.2570   0.09831   0.09023  -0.0509   0.0463   1.0000
  15.500   1.3394   0.08922   0.08060  -0.0425   0.0419   1.0000
  15.750   1.3509   0.09125   0.08288  -0.0420   0.0410   1.0000
  16.000   1.3709   0.09264   0.08447  -0.0408   0.0402   1.0000
  16.250   1.3939   0.09422   0.08627  -0.0396   0.0399   1.0000
  16.500   1.4079   0.09693   0.08922  -0.0389   0.0400   1.0000
  16.750   1.4130   0.10054   0.09310  -0.0388   0.0402   1.0000
  17.000   1.4129   0.10467   0.09750  -0.0390   0.0405   1.0000
  17.250   1.4080   0.10925   0.10234  -0.0397   0.0408   1.0000
  17.500   1.3999   0.11413   0.10747  -0.0408   0.0410   1.0000
  17.750   1.3905   0.11932   0.11289  -0.0422   0.0413   1.0000
  18.000   1.3754   0.12494   0.11875  -0.0444   0.0413   1.0000
  18.250   1.3647   0.13068   0.12469  -0.0465   0.0416   1.0000
  18.500   1.3541   0.13675   0.13095  -0.0488   0.0419   1.0000
  18.750   1.3436   0.14222   0.13663  -0.0514   0.0423   1.0000
  19.000   1.3223   0.14845   0.14308  -0.0558   0.0427   1.0000
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