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GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 621 AIRFOIL (goe621-il)
Reynolds number: 50,000
Max Cl/Cd: 27.65 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe621-il-50000-n5.txt
Download as CSV file: xf-goe621-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 621 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2583   0.14747   0.13992  -0.0438   1.0000   0.1349
 -12.250  -0.2679   0.14639   0.13893  -0.0438   1.0000   0.1357
 -12.000  -0.2754   0.14488   0.13749  -0.0435   1.0000   0.1360
 -11.750  -0.2824   0.14314   0.13584  -0.0430   1.0000   0.1362
 -11.500  -0.2883   0.14119   0.13396  -0.0423   1.0000   0.1363
 -11.250  -0.2926   0.13906   0.13190  -0.0413   1.0000   0.1363
 -10.250  -0.3172   0.12357   0.11657  -0.0392   1.0000   0.0941
 -10.000  -0.3190   0.12157   0.11463  -0.0377   0.9997   0.0934
  -9.750  -0.3019   0.11733   0.11037  -0.0413   0.9941   0.0920
  -9.500  -0.2894   0.11303   0.10605  -0.0451   0.9879   0.0903
  -9.250  -0.2791   0.10843   0.10144  -0.0496   0.9820   0.0887
  -9.000  -0.2736   0.10375   0.09675  -0.0538   0.9746   0.0875
  -8.750  -0.2664   0.09901   0.09200  -0.0587   0.9683   0.0871
  -8.500  -0.2616   0.09498   0.08797  -0.0622   0.9597   0.0875
  -8.250  -0.2580   0.09077   0.08377  -0.0661   0.9517   0.0881
  -8.000  -0.2594   0.08602   0.07903  -0.0705   0.9428   0.0879
  -7.750  -0.2714   0.08134   0.07436  -0.0737   0.9311   0.0875
  -7.500  -0.2878   0.07371   0.06666  -0.0802   0.9192   0.0866
  -7.250  -0.3054   0.06409   0.05672  -0.0882   0.9092   0.0859
  -7.000  -0.3193   0.05924   0.05159  -0.0888   0.8974   0.0859
  -6.750  -0.3085   0.05459   0.04655  -0.0918   0.8916   0.0866
  -6.500  -0.3087   0.05206   0.04379  -0.0903   0.8815   0.0875
  -6.250  -0.2900   0.04898   0.04032  -0.0919   0.8763   0.0899
  -6.000  -0.2842   0.04664   0.03758  -0.0905   0.8681   0.0918
  -5.750  -0.2677   0.04392   0.03423  -0.0906   0.8620   0.0942
  -5.500  -0.2393   0.04225   0.03242  -0.0917   0.8581   0.0964
  -5.250  -0.2295   0.04136   0.03140  -0.0894   0.8501   0.0982
  -5.000  -0.2065   0.04015   0.02996  -0.0893   0.8448   0.1015
  -4.750  -0.1767   0.03869   0.02804  -0.0901   0.8412   0.1065
  -4.500  -0.1642   0.03814   0.02749  -0.0881   0.8338   0.1099
  -4.250  -0.1414   0.03741   0.02668  -0.0876   0.8283   0.1147
  -4.000  -0.1110   0.03642   0.02538  -0.0882   0.8246   0.1220
  -3.750  -0.0929   0.03604   0.02506  -0.0869   0.8188   0.1283
  -3.500  -0.0737   0.03556   0.02440  -0.0857   0.8124   0.1372
  -3.250  -0.0446   0.03501   0.02385  -0.0861   0.8084   0.1498
  -3.000  -0.0104   0.03441   0.02321  -0.0872   0.8054   0.1674
  -2.750  -0.0036   0.03457   0.02345  -0.0843   0.7968   0.1791
  -2.500   0.0249   0.03429   0.02314  -0.0846   0.7922   0.2020
  -2.000   0.0684   0.03437   0.02335  -0.0831   0.7808   0.2519
  -1.750   0.0939   0.03440   0.02347  -0.0828   0.7756   0.2838
  -1.500   0.1278   0.03422   0.02333  -0.0836   0.7720   0.3199
  -1.250   0.1402   0.03464   0.02375  -0.0815   0.7641   0.3449
  -1.000   0.1661   0.03468   0.02381  -0.0811   0.7583   0.3749
  -0.750   0.2013   0.03446   0.02359  -0.0820   0.7545   0.4100
  -0.500   0.2138   0.03489   0.02404  -0.0798   0.7451   0.4346
  -0.250   0.2481   0.03450   0.02368  -0.0803   0.7388   0.4707
   0.000   0.2727   0.03434   0.02360  -0.0794   0.7300   0.5063
   0.250   0.3028   0.03385   0.02324  -0.0790   0.7219   0.5528
   0.500   0.3462   0.03262   0.02235  -0.0801   0.7178   0.6224
   1.000   0.4380   0.03179   0.02207  -0.0857   0.7017   1.0000
   1.250   0.4495   0.03243   0.02253  -0.0835   0.6909   1.0000
   1.500   0.4845   0.03224   0.02211  -0.0840   0.6846   1.0000
   2.000   0.5313   0.03261   0.02217  -0.0822   0.6671   1.0000
   2.500   0.5786   0.03290   0.02222  -0.0802   0.6491   1.0000
   3.000   0.6276   0.03303   0.02215  -0.0783   0.6304   1.0000
   3.250   0.6410   0.03355   0.02261  -0.0761   0.6185   1.0000
   3.500   0.6775   0.03305   0.02201  -0.0765   0.6114   1.0000
   3.750   0.6874   0.03368   0.02259  -0.0738   0.5977   1.0000
   4.000   0.7305   0.03284   0.02166  -0.0748   0.5919   1.0000
   4.250   0.7373   0.03359   0.02239  -0.0719   0.5772   1.0000
   4.500   0.7501   0.03413   0.02289  -0.0697   0.5637   1.0000
   4.750   0.7914   0.03326   0.02194  -0.0703   0.5569   1.0000
   5.000   0.8002   0.03398   0.02264  -0.0677   0.5420   1.0000
   5.250   0.8130   0.03458   0.02323  -0.0656   0.5282   1.0000
   5.500   0.8336   0.03480   0.02339  -0.0643   0.5162   1.0000
   5.750   0.8652   0.03438   0.02290  -0.0639   0.5066   1.0000
   6.000   0.8775   0.03512   0.02363  -0.0620   0.4930   1.0000
   6.250   0.8969   0.03549   0.02395  -0.0606   0.4812   1.0000
   6.500   0.9307   0.03501   0.02337  -0.0605   0.4721   1.0000
   6.750   0.9421   0.03592   0.02427  -0.0586   0.4594   1.0000
   7.000   0.9628   0.03631   0.02461  -0.0575   0.4488   1.0000
   7.250   0.9915   0.03623   0.02443  -0.0570   0.4392   1.0000
   7.500   1.0026   0.03727   0.02548  -0.0552   0.4280   1.0000
   7.750   1.0309   0.03729   0.02539  -0.0547   0.4190   1.0000
   8.000   1.0436   0.03826   0.02637  -0.0531   0.4085   1.0000
   8.250   1.0630   0.03887   0.02694  -0.0521   0.3992   1.0000
   8.500   1.0826   0.03948   0.02753  -0.0510   0.3899   1.0000
   8.750   1.0959   0.04050   0.02856  -0.0496   0.3807   1.0000
   9.000   1.1179   0.04100   0.02901  -0.0488   0.3720   1.0000
   9.250   1.1275   0.04230   0.03036  -0.0472   0.3633   1.0000
   9.500   1.1482   0.04291   0.03094  -0.0463   0.3549   1.0000
   9.750   1.1576   0.04428   0.03236  -0.0448   0.3467   1.0000
  10.000   1.1719   0.04532   0.03342  -0.0436   0.3385   1.0000
  10.250   1.1877   0.04634   0.03446  -0.0426   0.3310   1.0000
  10.500   1.1902   0.04824   0.03648  -0.0409   0.3234   1.0000
  10.750   1.2244   0.04808   0.03621  -0.0409   0.3164   1.0000
  11.000   1.2069   0.05141   0.03978  -0.0383   0.3090   1.0000
  11.250   1.2250   0.05228   0.04066  -0.0375   0.3023   1.0000
  11.500   1.2309   0.05414   0.04262  -0.0362   0.2959   1.0000
  11.750   1.2179   0.05756   0.04622  -0.0346   0.2890   1.0000
  12.000   1.2478   0.05744   0.04606  -0.0341   0.2832   1.0000
  12.250   1.2197   0.06245   0.05130  -0.0325   0.2769   1.0000
  12.500   1.2018   0.06690   0.05592  -0.0316   0.2704   1.0000
  12.750   1.2363   0.06613   0.05512  -0.0309   0.2659   1.0000
  13.000   1.1192   0.08308   0.07248  -0.0327   0.2558   1.0000
  13.250   1.1296   0.08484   0.07429  -0.0323   0.2511   1.0000
  13.500   1.1759   0.08176   0.07118  -0.0305   0.2487   1.0000
  13.750   1.0415   0.10585   0.09552  -0.0381   0.2337   1.0000
  14.000   1.0709   0.10439   0.09410  -0.0365   0.2320   1.0000
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