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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 500,000
Max Cl/Cd: 106.32 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe682-il-500000.txt
Download as CSV file: xf-goe682-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 682 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2784   0.08365   0.08156  -0.0436   0.9978   0.0368
  -9.250  -0.3591   0.09097   0.08875  -0.0414   1.0000   0.0362
  -9.000  -0.3733   0.08843   0.08626  -0.0399   1.0000   0.0363
  -8.750  -0.3668   0.08351   0.08135  -0.0422   0.9982   0.0370
  -8.500  -0.3452   0.08110   0.07894  -0.0447   0.9958   0.0375
  -8.250  -0.3250   0.07820   0.07603  -0.0484   0.9926   0.0383
  -8.000  -0.3536   0.04002   0.03724  -0.0960   0.9719   0.0369
  -7.750  -0.3364   0.03377   0.03061  -0.1002   0.9657   0.0356
  -7.500  -0.3178   0.02729   0.02341  -0.1040   0.9597   0.0360
  -7.250  -0.2930   0.02276   0.01829  -0.1065   0.9561   0.0370
  -7.000  -0.2707   0.02115   0.01652  -0.1062   0.9477   0.0376
  -6.750  -0.2405   0.01988   0.01511  -0.1073   0.9429   0.0383
  -6.500  -0.2141   0.01888   0.01397  -0.1073   0.9358   0.0390
  -6.250  -0.1865   0.01792   0.01286  -0.1074   0.9286   0.0399
  -6.000  -0.1602   0.01697   0.01174  -0.1072   0.9204   0.0408
  -5.750  -0.1335   0.01594   0.01050  -0.1070   0.9118   0.0415
  -5.500  -0.1085   0.01510   0.00948  -0.1063   0.9011   0.0422
  -5.250  -0.0819   0.01442   0.00862  -0.1059   0.8904   0.0428
  -5.000  -0.0550   0.01399   0.00803  -0.1054   0.8793   0.0434
  -4.750  -0.0315   0.01271   0.00663  -0.1046   0.8673   0.0448
  -4.500  -0.0057   0.01219   0.00606  -0.1041   0.8567   0.0459
  -4.250   0.0209   0.01179   0.00559  -0.1037   0.8468   0.0470
  -4.000   0.0467   0.01143   0.00516  -0.1031   0.8356   0.0482
  -3.750   0.0729   0.01110   0.00476  -0.1026   0.8252   0.0495
  -3.500   0.0994   0.01082   0.00439  -0.1021   0.8151   0.0509
  -3.250   0.1258   0.01066   0.00415  -0.1016   0.8040   0.0521
  -3.000   0.1507   0.01009   0.00355  -0.1009   0.7937   0.0553
  -2.750   0.1771   0.00990   0.00331  -0.1005   0.7842   0.0580
  -2.500   0.2034   0.00972   0.00309  -0.1000   0.7735   0.0610
  -2.250   0.2295   0.00947   0.00278  -0.0994   0.7636   0.0651
  -2.000   0.2557   0.00929   0.00257  -0.0990   0.7540   0.0711
  -1.750   0.2820   0.00910   0.00237  -0.0985   0.7442   0.0797
  -1.500   0.3083   0.00893   0.00220  -0.0980   0.7355   0.0938
  -1.250   0.3338   0.00863   0.00212  -0.0975   0.7252   0.1507
  -1.000   0.3598   0.00851   0.00210  -0.0971   0.7148   0.2015
  -0.750   0.3860   0.00845   0.00206  -0.0966   0.7040   0.2309
  -0.500   0.4122   0.00839   0.00203  -0.0962   0.6934   0.2583
  -0.250   0.4384   0.00830   0.00202  -0.0957   0.6836   0.2921
   0.000   0.4638   0.00817   0.00201  -0.0952   0.6738   0.3498
   0.250   0.4861   0.00767   0.00205  -0.0942   0.6629   0.5324
   0.500   0.5008   0.00688   0.00215  -0.0911   0.6529   0.8304
   0.750   0.5842   0.00677   0.00215  -0.1028   0.6389   1.0000
   1.000   0.6083   0.00687   0.00216  -0.1019   0.6285   1.0000
   1.250   0.6328   0.00695   0.00218  -0.1011   0.6178   1.0000
   1.500   0.6570   0.00706   0.00220  -0.1002   0.6071   1.0000
   1.750   0.6812   0.00718   0.00224  -0.0993   0.5961   1.0000
   2.000   0.7058   0.00727   0.00229  -0.0985   0.5847   1.0000
   2.250   0.7302   0.00738   0.00234  -0.0977   0.5732   1.0000
   2.500   0.7543   0.00750   0.00241  -0.0968   0.5609   1.0000
   2.750   0.7783   0.00764   0.00247  -0.0959   0.5472   1.0000
   3.000   0.8023   0.00778   0.00255  -0.0950   0.5324   1.0000
   3.500   0.8501   0.00810   0.00274  -0.0933   0.5024   1.0000
   3.750   0.8740   0.00828   0.00286  -0.0924   0.4876   1.0000
   4.000   0.8978   0.00848   0.00299  -0.0915   0.4731   1.0000
   4.250   0.9216   0.00868   0.00314  -0.0907   0.4591   1.0000
   4.500   0.9452   0.00889   0.00330  -0.0898   0.4450   1.0000
   4.750   0.9687   0.00912   0.00347  -0.0889   0.4310   1.0000
   5.000   0.9921   0.00935   0.00366  -0.0881   0.4168   1.0000
   5.250   1.0154   0.00959   0.00385  -0.0872   0.4028   1.0000
   5.500   1.0385   0.00984   0.00405  -0.0862   0.3872   1.0000
   5.750   1.0611   0.01011   0.00427  -0.0852   0.3689   1.0000
   6.000   1.0823   0.01045   0.00451  -0.0840   0.3466   1.0000
   6.250   1.1038   0.01079   0.00477  -0.0829   0.3225   1.0000
   6.500   1.1239   0.01120   0.00506  -0.0815   0.3002   1.0000
   6.750   1.1442   0.01161   0.00539  -0.0802   0.2806   1.0000
   7.000   1.1642   0.01203   0.00573  -0.0789   0.2647   1.0000
   7.250   1.1844   0.01243   0.00607  -0.0776   0.2522   1.0000
   7.750   1.2254   0.01316   0.00676  -0.0751   0.2334   1.0000
   8.000   1.2448   0.01356   0.00714  -0.0737   0.2246   1.0000
   8.250   1.2655   0.01387   0.00747  -0.0725   0.2172   1.0000
   8.500   1.2845   0.01426   0.00785  -0.0710   0.2090   1.0000
   8.750   1.3031   0.01462   0.00820  -0.0695   0.1994   1.0000
   9.000   1.3215   0.01494   0.00855  -0.0679   0.1911   1.0000
   9.250   1.3372   0.01537   0.00895  -0.0659   0.1822   1.0000
   9.500   1.3553   0.01571   0.00931  -0.0643   0.1718   1.0000
   9.750   1.3710   0.01616   0.00975  -0.0624   0.1585   1.0000
  10.000   1.3833   0.01680   0.01029  -0.0600   0.1370   1.0000
  10.250   1.3857   0.01800   0.01121  -0.0564   0.0976   1.0000
  10.500   1.3835   0.01952   0.01251  -0.0524   0.0673   1.0000
  10.750   1.3799   0.02121   0.01398  -0.0484   0.0383   1.0000
  11.000   1.3826   0.02260   0.01532  -0.0455   0.0290   1.0000
  11.250   1.3889   0.02382   0.01659  -0.0431   0.0258   1.0000
  11.500   1.3962   0.02500   0.01783  -0.0410   0.0240   1.0000
  11.750   1.3996   0.02653   0.01941  -0.0387   0.0223   1.0000
  12.000   1.4047   0.02798   0.02095  -0.0368   0.0213   1.0000
  12.250   1.4106   0.02945   0.02251  -0.0351   0.0206   1.0000
  12.500   1.4158   0.03104   0.02418  -0.0335   0.0197   1.0000
  12.750   1.4175   0.03298   0.02621  -0.0320   0.0190   1.0000
  13.000   1.4159   0.03533   0.02863  -0.0305   0.0183   1.0000
  13.250   1.4098   0.03822   0.03163  -0.0292   0.0179   1.0000
  13.500   1.4084   0.04081   0.03433  -0.0283   0.0176   1.0000
  13.750   1.4093   0.04327   0.03689  -0.0276   0.0173   1.0000
  14.000   1.4086   0.04600   0.03972  -0.0272   0.0169   1.0000
  14.250   1.4072   0.04891   0.04273  -0.0269   0.0166   1.0000
  14.500   1.4038   0.05214   0.04607  -0.0267   0.0163   1.0000
  14.750   1.4005   0.05547   0.04950  -0.0268   0.0160   1.0000
  15.000   1.3962   0.05907   0.05320  -0.0271   0.0157   1.0000
  15.250   1.3922   0.06270   0.05692  -0.0276   0.0155   1.0000
  15.500   1.3859   0.06676   0.06106  -0.0283   0.0151   1.0000
  15.750   1.3806   0.07078   0.06517  -0.0291   0.0149   1.0000
  16.000   1.3733   0.07515   0.06962  -0.0300   0.0147   1.0000
  16.250   1.3627   0.07986   0.07440  -0.0308   0.0143   1.0000
  16.500   1.3599   0.08380   0.07845  -0.0319   0.0141   1.0000
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