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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 100,000
Max Cl/Cd: 45.86 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe553-il-100000.txt
Download as CSV file: xf-goe553-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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  -0.2517   0.10345   0.09864  -0.0377   1.0000   0.1196
  -9.000  -0.2805   0.10289   0.09825  -0.0404   1.0000   0.1231
  -8.750  -0.3204   0.10300   0.09860  -0.0410   1.0000   0.1238
  -8.500  -0.2740   0.09642   0.09195  -0.0374   1.0000   0.1266
  -8.250  -0.2685   0.09453   0.09014  -0.0347   1.0000   0.1294
  -8.000  -0.2855   0.09410   0.08988  -0.0307   1.0000   0.1311
  -7.750  -0.2966   0.09333   0.08925  -0.0305   0.9953   0.1346
  -7.500  -0.2881   0.08764   0.08358  -0.0448   0.9769   0.1418
  -7.250  -0.2431   0.08396   0.07986  -0.0456   0.9724   0.1487
  -7.000  -0.2285   0.07768   0.07357  -0.0609   0.9536   0.1587
  -6.750  -0.1919   0.07472   0.07058  -0.0607   0.9456   0.1647
  -6.500  -0.1689   0.06895   0.06477  -0.0727   0.9316   0.1768
  -6.250  -0.1446   0.06366   0.05938  -0.0838   0.9182   0.1924
  -6.000  -0.1145   0.05983   0.05547  -0.0895   0.9086   0.2096
  -5.750  -0.0869   0.05792   0.05354  -0.0891   0.8962   0.2226
  -5.500  -0.0597   0.05517   0.05077  -0.0894   0.8863   0.2340
  -5.250  -0.0442   0.03739   0.03119  -0.1126   0.8692   0.1269
  -5.000  -0.0142   0.03310   0.02606  -0.1138   0.8585   0.1059
  -4.750   0.0118   0.03079   0.02345  -0.1140   0.8473   0.1035
  -4.500   0.0434   0.02879   0.02104  -0.1146   0.8387   0.1033
  -4.250   0.0682   0.02730   0.01923  -0.1141   0.8269   0.1025
  -4.000   0.0980   0.02579   0.01737  -0.1140   0.8179   0.1017
  -3.750   0.1249   0.02467   0.01600  -0.1134   0.8073   0.1020
  -3.500   0.1524   0.02372   0.01485  -0.1129   0.7974   0.1033
  -3.250   0.1812   0.02297   0.01388  -0.1124   0.7881   0.1067
  -3.000   0.2069   0.02224   0.01306  -0.1117   0.7777   0.1098
  -2.750   0.2353   0.02132   0.01217  -0.1112   0.7694   0.1138
  -2.500   0.2594   0.02086   0.01173  -0.1102   0.7586   0.1188
  -2.250   0.2876   0.02018   0.01103  -0.1096   0.7510   0.1271
  -2.000   0.3104   0.01985   0.01077  -0.1086   0.7399   0.1409
  -1.750   0.3369   0.01903   0.01016  -0.1080   0.7320   0.1798
  -1.500   0.3512   0.01787   0.01064  -0.1053   0.7220   0.5964
  -1.250   0.3737   0.01804   0.01081  -0.1029   0.7140   0.6610
  -1.000   0.3931   0.01822   0.01104  -0.1004   0.7039   0.7065
  -0.750   0.4138   0.01831   0.01112  -0.0979   0.6959   0.7513
  -0.500   0.4290   0.01832   0.01124  -0.0942   0.6862   0.7982
  -0.250   0.4458   0.01820   0.01115  -0.0905   0.6788   0.8464
   0.000   0.4647   0.01811   0.01115  -0.0879   0.6690   0.8909
   0.250   0.5066   0.01803   0.01097  -0.0898   0.6605   0.9382
   0.500   0.5646   0.01808   0.01088  -0.0961   0.6493   1.0000
   0.750   0.5883   0.01843   0.01106  -0.0966   0.6403   1.0000
   1.000   0.6175   0.01872   0.01117  -0.0975   0.6315   1.0000
   1.250   0.6455   0.01912   0.01142  -0.0981   0.6228   1.0000
   1.500   0.6739   0.01943   0.01157  -0.0984   0.6140   1.0000
   1.750   0.7011   0.01982   0.01184  -0.0985   0.6056   1.0000
   2.000   0.7280   0.02017   0.01208  -0.0984   0.5968   1.0000
   2.250   0.7559   0.02055   0.01233  -0.0985   0.5898   1.0000
   2.500   0.7801   0.02104   0.01279  -0.0981   0.5809   1.0000
   2.750   0.8106   0.02126   0.01283  -0.0982   0.5751   1.0000
   3.000   0.8316   0.02188   0.01352  -0.0975   0.5654   1.0000
   3.250   0.8612   0.02204   0.01353  -0.0975   0.5589   1.0000
   3.500   0.8832   0.02266   0.01418  -0.0968   0.5504   1.0000
   3.750   0.9108   0.02288   0.01433  -0.0965   0.5434   1.0000
   4.000   0.9354   0.02329   0.01471  -0.0960   0.5357   1.0000
   4.250   0.9611   0.02351   0.01489  -0.0955   0.5276   1.0000
   4.500   0.9884   0.02373   0.01506  -0.0952   0.5209   1.0000
   4.750   1.0107   0.02419   0.01556  -0.0945   0.5125   1.0000
   5.000   1.0426   0.02412   0.01533  -0.0946   0.5069   1.0000
   5.250   1.0606   0.02477   0.01613  -0.0933   0.4975   1.0000
   5.500   1.0908   0.02478   0.01602  -0.0934   0.4916   1.0000
   5.750   1.1104   0.02550   0.01686  -0.0923   0.4841   1.0000
   6.000   1.1363   0.02581   0.01717  -0.0920   0.4777   1.0000
   6.250   1.1648   0.02606   0.01737  -0.0919   0.4724   1.0000
   6.500   1.1821   0.02687   0.01833  -0.0906   0.4644   1.0000
   6.750   1.2127   0.02691   0.01828  -0.0907   0.4587   1.0000
   7.000   1.2298   0.02773   0.01927  -0.0894   0.4509   1.0000
   7.250   1.2569   0.02791   0.01943  -0.0890   0.4440   1.0000
   7.500   1.2791   0.02845   0.02003  -0.0882   0.4369   1.0000
   7.750   1.3012   0.02889   0.02054  -0.0874   0.4290   1.0000
   8.000   1.3287   0.02918   0.02080  -0.0872   0.4224   1.0000
   8.250   1.3448   0.02995   0.02173  -0.0857   0.4138   1.0000
   8.500   1.3772   0.03003   0.02171  -0.0860   0.4073   1.0000
   8.750   1.3875   0.03107   0.02298  -0.0838   0.3980   1.0000
   9.000   1.4212   0.03113   0.02291  -0.0844   0.3911   1.0000
   9.250   1.4291   0.03221   0.02424  -0.0818   0.3814   1.0000
   9.500   1.4563   0.03241   0.02440  -0.0815   0.3729   1.0000
   9.750   1.4717   0.03298   0.02507  -0.0798   0.3632   1.0000
  10.000   1.4889   0.03355   0.02569  -0.0783   0.3538   1.0000
  10.250   1.5162   0.03348   0.02554  -0.0780   0.3446   1.0000
  10.500   1.5215   0.03457   0.02684  -0.0752   0.3356   1.0000
  10.750   1.5537   0.03452   0.02665  -0.0756   0.3277   1.0000
  11.000   1.5517   0.03599   0.02841  -0.0720   0.3200   1.0000
  11.250   1.5804   0.03602   0.02835  -0.0720   0.3124   1.0000
  11.500   1.5778   0.03742   0.03000  -0.0684   0.3053   1.0000
  11.750   1.5963   0.03779   0.03038  -0.0672   0.2981   1.0000
  12.000   1.5997   0.03881   0.03153  -0.0643   0.2916   1.0000
  12.250   1.5981   0.03981   0.03267  -0.0609   0.2850   1.0000
  12.500   1.6140   0.04016   0.03300  -0.0594   0.2778   1.0000
  12.750   1.5989   0.04206   0.03513  -0.0553   0.2721   1.0000
  13.000   1.6243   0.04183   0.03480  -0.0548   0.2641   1.0000
  13.250   1.5994   0.04463   0.03789  -0.0509   0.2591   1.0000
  13.500   1.6144   0.04480   0.03801  -0.0496   0.2506   1.0000
  13.750   1.5926   0.04795   0.04142  -0.0471   0.2451   1.0000
  14.000   1.5983   0.04885   0.04230  -0.0458   0.2362   1.0000
  14.250   1.5759   0.05266   0.04634  -0.0444   0.2298   1.0000
  14.500   1.5793   0.05395   0.04756  -0.0435   0.2196   1.0000
  14.750   1.5526   0.05885   0.05270  -0.0432   0.2124   1.0000
  15.000   1.1324   0.13551   0.12976  -0.0737   0.2091   1.0000
  15.250   1.2234   0.11924   0.11371  -0.0649   0.2084   1.0000
  15.500   1.2020   0.12686   0.12138  -0.0681   0.1957   1.0000
  15.750   1.5029   0.07414   0.06796  -0.0440   0.1677   1.0000
  16.000   1.4882   0.07897   0.07280  -0.0448   0.1569   1.0000
  16.250   1.4796   0.08306   0.07683  -0.0455   0.1466   1.0000
  16.500   1.4697   0.08753   0.08129  -0.0466   0.1377   1.0000
  16.750   1.4518   0.09361   0.08753  -0.0486   0.1310   1.0000
  17.000   1.4526   0.09657   0.09037  -0.0493   0.1233   1.0000
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