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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 100,000
Max Cl/Cd: 55.15 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe488-il-100000.txt
Download as CSV file: xf-goe488-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 488 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4138   0.10157   0.09653  -0.0267   1.0000   0.0832
  -8.250  -0.4313   0.10086   0.09596  -0.0286   1.0000   0.0838
  -8.000  -0.4418   0.09937   0.09453  -0.0328   1.0000   0.0841
  -7.750  -0.4117   0.09160   0.08673  -0.0250   1.0000   0.0875
  -7.500  -0.4096   0.08905   0.08422  -0.0236   1.0000   0.0909
  -7.250  -0.4149   0.08682   0.08206  -0.0235   1.0000   0.0940
  -7.000  -0.4241   0.08504   0.08036  -0.0267   1.0000   0.0971
  -6.750  -0.4352   0.08443   0.07965  -0.0343   1.0000   0.0985
  -6.500  -0.4259   0.07856   0.07394  -0.0259   1.0000   0.1011
  -6.250  -0.4224   0.07595   0.07136  -0.0237   1.0000   0.1039
  -6.000  -0.4205   0.07342   0.06883  -0.0236   1.0000   0.1080
  -5.750  -0.4176   0.07076   0.06598  -0.0300   1.0000   0.1136
  -5.500  -0.4134   0.06725   0.06258  -0.0258   1.0000   0.1156
  -5.250  -0.4071   0.06473   0.06008  -0.0239   1.0000   0.1197
  -5.000  -0.3949   0.06174   0.05687  -0.0277   1.0000   0.1288
  -4.750  -0.3887   0.05905   0.05428  -0.0244   1.0000   0.1330
  -4.500  -0.3729   0.05628   0.05127  -0.0270   1.0000   0.1437
  -4.250  -0.3537   0.05532   0.04997  -0.0286   1.0000   0.1569
  -4.000  -0.3464   0.05091   0.04575  -0.0261   1.0000   0.1592
  -3.750  -0.3325   0.04865   0.04347  -0.0250   1.0000   0.1673
  -3.500  -0.3163   0.04601   0.04073  -0.0250   1.0000   0.1770
  -3.250  -0.2993   0.04380   0.03842  -0.0248   1.0000   0.1913
  -3.000  -0.2824   0.04173   0.03628  -0.0243   1.0000   0.2076
  -2.750  -0.2641   0.03972   0.03416  -0.0239   1.0000   0.2234
  -2.500  -0.2439   0.03799   0.03225  -0.0241   1.0000   0.2472
  -2.250  -0.1819   0.03143   0.02392  -0.0289   1.0000   0.1272
  -2.000  -0.1551   0.02785   0.02001  -0.0288   1.0000   0.1100
  -1.750  -0.1311   0.02615   0.01801  -0.0282   1.0000   0.1084
  -1.500  -0.1070   0.02466   0.01621  -0.0275   1.0000   0.1067
  -1.250  -0.0823   0.02322   0.01437  -0.0267   1.0000   0.1033
  -1.000  -0.0585   0.02220   0.01303  -0.0259   1.0000   0.1021
  -0.750  -0.0357   0.02145   0.01214  -0.0250   1.0000   0.1025
  -0.500  -0.0136   0.02088   0.01149  -0.0242   1.0000   0.1042
  -0.250   0.0368   0.02049   0.01100  -0.0286   0.9903   0.1103
   0.000   0.0863   0.02009   0.01070  -0.0329   0.9797   0.1220
   0.250   0.1338   0.01965   0.01039  -0.0366   0.9707   0.1384
   0.500   0.1939   0.01664   0.00998  -0.0426   0.9677   1.0000
   0.750   0.2414   0.01694   0.00992  -0.0465   0.9572   1.0000
   1.000   0.2837   0.01711   0.00993  -0.0493   0.9452   1.0000
   1.250   0.3270   0.01722   0.00994  -0.0523   0.9332   1.0000
   1.500   0.3722   0.01723   0.00988  -0.0554   0.9209   1.0000
   1.750   0.4198   0.01712   0.00975  -0.0589   0.9090   1.0000
   2.000   0.4747   0.01680   0.00944  -0.0634   0.8985   1.0000
   2.250   0.5229   0.01635   0.00904  -0.0665   0.8846   1.0000
   2.500   0.5690   0.01580   0.00856  -0.0689   0.8697   1.0000
   2.750   0.6045   0.01530   0.00814  -0.0690   0.8489   1.0000
   3.000   0.6470   0.01454   0.00746  -0.0700   0.8261   1.0000
   3.250   0.6758   0.01396   0.00690  -0.0684   0.7885   1.0000
   3.500   0.7043   0.01349   0.00636  -0.0667   0.7347   1.0000
   3.750   0.7326   0.01333   0.00592  -0.0652   0.6615   1.0000
   4.000   0.7578   0.01374   0.00590  -0.0637   0.5941   1.0000
   4.250   0.7798   0.01434   0.00619  -0.0621   0.5450   1.0000
   4.500   0.8020   0.01491   0.00656  -0.0608   0.5096   1.0000
   4.750   0.8245   0.01548   0.00698  -0.0595   0.4812   1.0000
   5.000   0.8468   0.01608   0.00746  -0.0583   0.4553   1.0000
   5.250   0.8691   0.01671   0.00795  -0.0572   0.4311   1.0000
   5.500   0.8908   0.01732   0.00851  -0.0559   0.4067   1.0000
   5.750   0.9130   0.01799   0.00911  -0.0548   0.3850   1.0000
   6.000   0.9347   0.01863   0.00977  -0.0537   0.3629   1.0000
   6.250   0.9546   0.01919   0.01033  -0.0522   0.3383   1.0000
   6.500   0.9733   0.01967   0.01075  -0.0505   0.3131   1.0000
   6.750   0.9921   0.02006   0.01126  -0.0488   0.2893   1.0000
   7.000   1.0101   0.02035   0.01169  -0.0470   0.2643   1.0000
   7.250   1.0273   0.02054   0.01199  -0.0451   0.2339   1.0000
   7.500   1.0434   0.02092   0.01234  -0.0431   0.1902   1.0000
   7.750   1.0496   0.02297   0.01369  -0.0400   0.1008   1.0000
   8.000   1.0590   0.02502   0.01546  -0.0370   0.0704   1.0000
   8.250   1.0696   0.02684   0.01726  -0.0342   0.0624   1.0000
   8.500   1.0826   0.02860   0.01906  -0.0319   0.0574   1.0000
   8.750   1.0994   0.03093   0.02137  -0.0303   0.0534   1.0000
   9.000   1.1185   0.03264   0.02328  -0.0288   0.0494   1.0000
   9.250   1.1388   0.03478   0.02552  -0.0277   0.0468   1.0000
   9.500   1.1603   0.03743   0.02829  -0.0269   0.0452   1.0000
   9.750   1.1811   0.04085   0.03190  -0.0262   0.0442   1.0000
  10.000   1.1968   0.04462   0.03599  -0.0248   0.0438   1.0000
  10.250   1.2066   0.04814   0.03993  -0.0228   0.0437   1.0000
  10.500   1.2109   0.05199   0.04417  -0.0205   0.0435   1.0000
  10.750   1.2083   0.05631   0.04885  -0.0178   0.0433   1.0000
  11.000   1.2016   0.05920   0.05212  -0.0146   0.0431   1.0000
  11.250   1.1909   0.06234   0.05559  -0.0113   0.0430   1.0000
  11.500   1.1754   0.06548   0.05899  -0.0079   0.0430   1.0000
  11.750   1.1599   0.06951   0.06324  -0.0055   0.0432   1.0000
  12.000   1.1464   0.07284   0.06681  -0.0037   0.0435   1.0000
  12.250   1.1262   0.07644   0.07062  -0.0028   0.0436   1.0000
  12.500   1.1040   0.08055   0.07495  -0.0032   0.0439   1.0000
  12.750   0.8953   0.09493   0.09025  -0.0129   0.0499   1.0000
  13.000   0.8496   0.10785   0.10326  -0.0213   0.0516   1.0000
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