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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.52 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe682-il-1000000.txt
Download as CSV file: xf-goe682-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2724   0.12008   0.11844  -0.0386   1.0000   0.0208
 -12.250  -0.2735   0.11627   0.11464  -0.0393   1.0000   0.0209
 -12.000  -0.8303   0.03271   0.03039  -0.0866   0.9971   0.0196
 -11.750  -0.8052   0.02997   0.02742  -0.0903   0.9947   0.0201
 -11.500  -0.7799   0.02800   0.02524  -0.0926   0.9922   0.0205
 -11.250  -0.7496   0.02750   0.02465  -0.0939   0.9900   0.0209
 -11.000  -0.7312   0.02365   0.02045  -0.0967   0.9863   0.0216
 -10.750  -0.6989   0.02315   0.01993  -0.0983   0.9849   0.0220
 -10.500  -0.6658   0.02268   0.01943  -0.1000   0.9837   0.0224
 -10.250  -0.6353   0.02229   0.01900  -0.1010   0.9813   0.0229
 -10.000  -0.6073   0.02164   0.01827  -0.1017   0.9778   0.0235
  -9.750  -0.5773   0.02070   0.01720  -0.1029   0.9753   0.0241
  -9.500  -0.5451   0.01990   0.01626  -0.1045   0.9734   0.0247
  -9.250  -0.5121   0.01922   0.01544  -0.1060   0.9716   0.0251
  -9.000  -0.4890   0.01705   0.01298  -0.1066   0.9664   0.0258
  -8.750  -0.4611   0.01636   0.01225  -0.1070   0.9612   0.0264
  -8.500  -0.4291   0.01598   0.01184  -0.1081   0.9576   0.0270
  -8.250  -0.4022   0.01546   0.01124  -0.1081   0.9510   0.0275
  -8.000  -0.3743   0.01492   0.01060  -0.1083   0.9442   0.0280
  -7.750  -0.3476   0.01439   0.00997  -0.1081   0.9366   0.0286
  -7.500  -0.3207   0.01400   0.00949  -0.1080   0.9285   0.0293
  -7.250  -0.2947   0.01355   0.00893  -0.1076   0.9200   0.0298
  -7.000  -0.2681   0.01316   0.00843  -0.1073   0.9112   0.0301
  -6.750  -0.2426   0.01276   0.00793  -0.1068   0.9009   0.0304
  -6.500  -0.2205   0.01147   0.00647  -0.1059   0.8898   0.0313
  -6.250  -0.1948   0.01111   0.00605  -0.1054   0.8785   0.0321
  -6.000  -0.1692   0.01081   0.00567  -0.1048   0.8661   0.0326
  -5.750  -0.1435   0.01051   0.00530  -0.1043   0.8537   0.0332
  -5.500  -0.1177   0.01024   0.00495  -0.1037   0.8416   0.0339
  -5.250  -0.0918   0.00998   0.00460  -0.1032   0.8303   0.0346
  -5.000  -0.0657   0.00973   0.00428  -0.1027   0.8192   0.0352
  -4.750  -0.0393   0.00953   0.00401  -0.1023   0.8086   0.0358
  -4.500  -0.0126   0.00943   0.00383  -0.1018   0.7978   0.0363
  -4.250   0.0121   0.00890   0.00322  -0.1011   0.7866   0.0376
  -4.000   0.0383   0.00866   0.00294  -0.1007   0.7762   0.0387
  -3.750   0.0648   0.00851   0.00274  -0.1003   0.7659   0.0398
  -3.500   0.0914   0.00839   0.00256  -0.0999   0.7551   0.0410
  -3.250   0.1182   0.00827   0.00240  -0.0995   0.7446   0.0424
  -3.000   0.1450   0.00820   0.00227  -0.0991   0.7343   0.0434
  -2.750   0.1713   0.00798   0.00200  -0.0986   0.7242   0.0463
  -2.500   0.1983   0.00789   0.00189  -0.0983   0.7149   0.0492
  -2.250   0.2250   0.00784   0.00179  -0.0979   0.7050   0.0516
  -2.000   0.2516   0.00771   0.00164  -0.0975   0.6939   0.0569
  -1.750   0.2785   0.00765   0.00156  -0.0972   0.6833   0.0618
  -1.500   0.3049   0.00757   0.00145  -0.0967   0.6729   0.0702
  -1.250   0.3318   0.00749   0.00137  -0.0964   0.6633   0.0809
  -1.000   0.3581   0.00732   0.00131  -0.0960   0.6544   0.1161
  -0.750   0.3840   0.00718   0.00130  -0.0956   0.6444   0.1720
  -0.500   0.4110   0.00714   0.00129  -0.0953   0.6345   0.1962
  -0.250   0.4376   0.00712   0.00129  -0.0950   0.6253   0.2164
   0.000   0.4645   0.00709   0.00129  -0.0947   0.6149   0.2386
   0.250   0.4911   0.00705   0.00130  -0.0944   0.6045   0.2659
   0.500   0.5171   0.00699   0.00132  -0.0939   0.5940   0.3114
   0.750   0.5427   0.00679   0.00135  -0.0935   0.5837   0.4015
   1.000   0.5647   0.00629   0.00142  -0.0925   0.5741   0.6253
   1.250   0.5803   0.00566   0.00154  -0.0895   0.5641   0.8971
   1.500   0.6603   0.00571   0.00160  -0.1010   0.5475   0.9991
   1.750   0.6873   0.00583   0.00164  -0.1007   0.5327   1.0000
   2.000   0.7114   0.00595   0.00168  -0.0999   0.5172   1.0000
   2.250   0.7355   0.00609   0.00174  -0.0990   0.5009   1.0000
   2.500   0.7596   0.00624   0.00181  -0.0981   0.4853   1.0000
   2.750   0.7836   0.00640   0.00189  -0.0973   0.4703   1.0000
   3.250   0.8320   0.00671   0.00208  -0.0956   0.4436   1.0000
   3.500   0.8564   0.00687   0.00218  -0.0949   0.4315   1.0000
   3.750   0.8806   0.00703   0.00229  -0.0941   0.4194   1.0000
   4.000   0.9047   0.00721   0.00241  -0.0933   0.4071   1.0000
   4.250   0.9292   0.00738   0.00253  -0.0925   0.3951   1.0000
   4.500   0.9538   0.00754   0.00265  -0.0919   0.3831   1.0000
   4.750   0.9780   0.00773   0.00279  -0.0911   0.3691   1.0000
   5.000   1.0016   0.00796   0.00295  -0.0903   0.3512   1.0000
   5.250   1.0244   0.00824   0.00312  -0.0893   0.3285   1.0000
   5.500   1.0465   0.00857   0.00333  -0.0882   0.3027   1.0000
   5.750   1.0686   0.00890   0.00356  -0.0872   0.2799   1.0000
   6.500   1.1349   0.00988   0.00429  -0.0841   0.2324   1.0000
   6.750   1.1576   0.01015   0.00453  -0.0831   0.2233   1.0000
   7.000   1.1805   0.01041   0.00476  -0.0823   0.2158   1.0000
   7.250   1.2034   0.01066   0.00500  -0.0814   0.2088   1.0000
   7.500   1.2260   0.01092   0.00524  -0.0805   0.2010   1.0000
   7.750   1.2485   0.01117   0.00549  -0.0795   0.1944   1.0000
   8.000   1.2708   0.01143   0.00573  -0.0786   0.1865   1.0000
   8.250   1.2926   0.01171   0.00599  -0.0776   0.1776   1.0000
   8.500   1.3131   0.01205   0.00628  -0.0764   0.1674   1.0000
   8.750   1.3336   0.01237   0.00657  -0.0751   0.1556   1.0000
   9.000   1.3516   0.01282   0.00693  -0.0735   0.1388   1.0000
   9.250   1.3622   0.01360   0.00750  -0.0707   0.1061   1.0000
   9.750   1.3732   0.01539   0.00898  -0.0633   0.0579   1.0000
  10.000   1.3740   0.01659   0.00997  -0.0591   0.0304   1.0000
  10.250   1.3819   0.01747   0.01081  -0.0561   0.0218   1.0000
  10.500   1.3941   0.01814   0.01149  -0.0538   0.0194   1.0000
  10.750   1.4051   0.01890   0.01228  -0.0515   0.0176   1.0000
  11.000   1.4181   0.01956   0.01300  -0.0495   0.0166   1.0000
  11.250   1.4294   0.02033   0.01381  -0.0475   0.0157   1.0000
  11.500   1.4389   0.02126   0.01477  -0.0453   0.0149   1.0000
  11.750   1.4466   0.02233   0.01592  -0.0430   0.0141   1.0000
  12.000   1.4576   0.02322   0.01687  -0.0413   0.0137   1.0000
  12.250   1.4671   0.02425   0.01797  -0.0395   0.0134   1.0000
  12.500   1.4763   0.02535   0.01912  -0.0378   0.0130   1.0000
  12.750   1.4839   0.02660   0.02043  -0.0362   0.0125   1.0000
  13.000   1.4902   0.02801   0.02191  -0.0346   0.0121   1.0000
  13.250   1.4927   0.02979   0.02376  -0.0329   0.0117   1.0000
  13.500   1.4891   0.03219   0.02626  -0.0311   0.0113   1.0000
  13.750   1.4958   0.03380   0.02795  -0.0301   0.0112   1.0000
  14.000   1.4997   0.03572   0.02995  -0.0291   0.0110   1.0000
  14.250   1.5056   0.03752   0.03182  -0.0283   0.0107   1.0000
  14.500   1.5064   0.03989   0.03428  -0.0275   0.0105   1.0000
  14.750   1.5078   0.04228   0.03676  -0.0269   0.0104   1.0000
  15.000   1.5076   0.04494   0.03951  -0.0265   0.0101   1.0000
  15.250   1.5073   0.04771   0.04235  -0.0263   0.0100   1.0000
  15.500   1.5057   0.05072   0.04544  -0.0262   0.0097   1.0000
  15.750   1.5020   0.05405   0.04887  -0.0263   0.0096   1.0000
  16.000   1.4966   0.05775   0.05266  -0.0266   0.0095   1.0000
  16.250   1.4904   0.06166   0.05666  -0.0272   0.0093   1.0000
  16.500   1.4805   0.06618   0.06128  -0.0280   0.0092   1.0000
  16.750   1.4704   0.07090   0.06612  -0.0291   0.0092   1.0000
  17.000   1.4560   0.07641   0.07173  -0.0306   0.0090   1.0000
  17.250   1.4419   0.08199   0.07743  -0.0322   0.0089   1.0000
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