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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 100,000
Max Cl/Cd: 65.12 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe483-il-100000-n5.txt
Download as CSV file: xf-goe483-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2838   0.10009   0.09576  -0.0268   1.0000   0.0314
  -7.000  -0.2885   0.09887   0.09464  -0.0262   1.0000   0.0315
  -6.750  -0.2951   0.09784   0.09370  -0.0255   1.0000   0.0316
  -6.500  -0.2843   0.09530   0.09119  -0.0292   0.9964   0.0317
  -6.250  -0.2575   0.09054   0.08643  -0.0361   0.9892   0.0319
  -6.000  -0.2483   0.08471   0.08062  -0.0318   0.9862   0.0336
  -5.750  -0.2214   0.08062   0.07650  -0.0373   0.9786   0.0355
  -5.500  -0.1911   0.07645   0.07230  -0.0442   0.9696   0.0368
  -5.250  -0.1580   0.07234   0.06813  -0.0517   0.9607   0.0384
  -5.000  -0.1002   0.06856   0.06415  -0.0677   0.9529   0.0414
  -4.750  -0.0627   0.06452   0.06000  -0.0751   0.9444   0.0416
  -4.250  -0.0188   0.05482   0.05023  -0.0790   0.9310   0.0284
  -4.000   0.0197   0.05042   0.04571  -0.0855   0.9249   0.0261
  -3.750   0.0564   0.04659   0.04172  -0.0909   0.9167   0.0267
  -3.500   0.0971   0.04253   0.03747  -0.0966   0.9102   0.0278
  -3.250   0.1356   0.03846   0.03316  -0.1013   0.9026   0.0272
  -3.000   0.1766   0.03416   0.02855  -0.1058   0.8961   0.0269
  -2.750   0.2162   0.02958   0.02356  -0.1095   0.8887   0.0273
  -2.500   0.2587   0.02389   0.01705  -0.1132   0.8830   0.0301
  -2.250   0.2919   0.02067   0.01306  -0.1143   0.8750   0.0331
  -2.000   0.3232   0.01910   0.01108  -0.1147   0.8674   0.0387
  -1.750   0.3533   0.01794   0.00963  -0.1149   0.8592   0.0484
  -1.500   0.3817   0.01723   0.00868  -0.1147   0.8498   0.0629
  -1.250   0.4111   0.01648   0.00771  -0.1145   0.8412   0.0764
  -1.000   0.4392   0.01612   0.00714  -0.1142   0.8314   0.0956
  -0.750   0.4665   0.01564   0.00659  -0.1137   0.8206   0.1118
  -0.500   0.4933   0.01535   0.00627  -0.1132   0.8097   0.1313
  -0.250   0.5203   0.01526   0.00611  -0.1126   0.7986   0.1557
   0.000   0.5473   0.01519   0.00593  -0.1121   0.7871   0.1790
   0.250   0.5737   0.01509   0.00577  -0.1115   0.7741   0.1979
   0.500   0.6000   0.01497   0.00558  -0.1108   0.7610   0.2166
   0.750   0.6263   0.01486   0.00540  -0.1102   0.7477   0.2359
   1.000   0.6523   0.01474   0.00524  -0.1096   0.7339   0.2548
   1.250   0.6784   0.01465   0.00511  -0.1091   0.7197   0.2779
   1.500   0.7045   0.01454   0.00501  -0.1085   0.7051   0.3020
   1.750   0.7305   0.01443   0.00494  -0.1081   0.6901   0.3357
   2.250   0.7839   0.01339   0.00484  -0.1071   0.6591   1.0000
   2.500   0.8095   0.01355   0.00490  -0.1065   0.6428   1.0000
   2.750   0.8351   0.01372   0.00497  -0.1059   0.6264   1.0000
   3.000   0.8606   0.01391   0.00507  -0.1052   0.6101   1.0000
   3.250   0.8861   0.01412   0.00520  -0.1046   0.5943   1.0000
   3.500   0.9114   0.01436   0.00541  -0.1040   0.5789   1.0000
   3.750   0.9367   0.01463   0.00562  -0.1034   0.5640   1.0000
   4.000   0.9618   0.01492   0.00588  -0.1028   0.5493   1.0000
   4.250   0.9868   0.01524   0.00622  -0.1022   0.5348   1.0000
   4.500   1.0116   0.01558   0.00657  -0.1016   0.5202   1.0000
   4.750   1.0362   0.01593   0.00695  -0.1009   0.5056   1.0000
   5.000   1.0608   0.01629   0.00738  -0.1003   0.4911   1.0000
   5.250   1.0852   0.01667   0.00788  -0.0996   0.4767   1.0000
   5.500   1.1095   0.01705   0.00838  -0.0990   0.4625   1.0000
   5.750   1.1325   0.01744   0.00883  -0.0980   0.4430   1.0000
   6.000   1.1510   0.01782   0.00916  -0.0963   0.3961   1.0000
   6.250   1.1679   0.01848   0.00960  -0.0945   0.3378   1.0000
   6.500   1.1804   0.01977   0.01040  -0.0924   0.2418   1.0000
   6.750   1.1762   0.02346   0.01247  -0.0889   0.0388   1.0000
   7.000   1.1898   0.02514   0.01415  -0.0869   0.0257   1.0000
   7.250   1.2053   0.02647   0.01570  -0.0850   0.0211   1.0000
   7.500   1.2192   0.02792   0.01739  -0.0831   0.0189   1.0000
   7.750   1.2291   0.02962   0.01935  -0.0807   0.0177   1.0000
   8.000   1.2327   0.03171   0.02169  -0.0777   0.0167   1.0000
   8.250   1.2404   0.03325   0.02340  -0.0752   0.0158   1.0000
   8.500   1.2450   0.03485   0.02518  -0.0723   0.0149   1.0000
   8.750   1.2483   0.03669   0.02716  -0.0695   0.0142   1.0000
   9.000   1.2528   0.03871   0.02930  -0.0669   0.0138   1.0000
   9.250   1.2612   0.04083   0.03162  -0.0647   0.0135   1.0000
   9.500   1.2755   0.04312   0.03403  -0.0630   0.0131   1.0000
   9.750   1.2944   0.04561   0.03669  -0.0617   0.0129   1.0000
  10.000   1.3128   0.04840   0.03972  -0.0605   0.0126   1.0000
  10.250   1.3253   0.05122   0.04279  -0.0590   0.0121   1.0000
  10.500   1.3321   0.05410   0.04592  -0.0574   0.0114   1.0000
  10.750   1.3352   0.05714   0.04920  -0.0558   0.0109   1.0000
  11.000   1.3346   0.06041   0.05275  -0.0541   0.0106   1.0000
  11.250   1.3309   0.06392   0.05654  -0.0526   0.0105   1.0000
  11.500   1.3246   0.06764   0.06057  -0.0513   0.0106   1.0000
  11.750   1.3159   0.07161   0.06483  -0.0505   0.0106   1.0000
  12.000   1.3045   0.07595   0.06947  -0.0503   0.0107   1.0000
  12.250   1.2908   0.08065   0.07445  -0.0507   0.0108   1.0000
  12.500   1.2759   0.08580   0.07987  -0.0518   0.0109   1.0000
  12.750   1.2603   0.09137   0.08570  -0.0537   0.0110   1.0000
  13.000   1.2440   0.09746   0.09204  -0.0563   0.0111   1.0000
  13.250   1.2274   0.10399   0.09879  -0.0596   0.0112   1.0000
  13.500   1.2107   0.11104   0.10605  -0.0637   0.0113   1.0000
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