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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 500,000
Max Cl/Cd: 96.45 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe488-il-500000.txt
Download as CSV file: xf-goe488-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4100   0.09642   0.09408  -0.0257   1.0000   0.0251
  -8.750  -0.4146   0.09336   0.09106  -0.0286   1.0000   0.0256
  -8.500  -0.4166   0.09036   0.08809  -0.0292   1.0000   0.0257
  -8.250  -0.3588   0.07302   0.07095  -0.0317   1.0000   0.0262
  -8.000  -0.3666   0.07021   0.06818  -0.0295   1.0000   0.0265
  -7.750  -0.3779   0.06860   0.06662  -0.0264   1.0000   0.0268
  -7.500  -0.3951   0.06723   0.06530  -0.0232   0.9997   0.0269
  -7.250  -0.3810   0.06344   0.06150  -0.0265   0.9969   0.0274
  -7.000  -0.4475   0.06971   0.06759  -0.0318   0.9971   0.0268
  -6.750  -0.4246   0.06694   0.06480  -0.0348   0.9949   0.0276
  -6.500  -0.4004   0.06356   0.06137  -0.0391   0.9920   0.0289
  -6.250  -0.3587   0.05781   0.05544  -0.0497   0.9877   0.0335
  -6.000  -0.3245   0.05163   0.04904  -0.0568   0.9848   0.0338
  -5.750  -0.3087   0.04218   0.03937  -0.0624   0.9798   0.0352
  -5.500  -0.2812   0.04045   0.03758  -0.0643   0.9761   0.0361
  -5.250  -0.2493   0.03850   0.03555  -0.0671   0.9735   0.0381
  -5.000  -0.2052   0.03534   0.03196  -0.0708   0.9714   0.0440
  -4.750  -0.1560   0.01228   0.00873  -0.0753   0.9617   0.0465
  -4.500  -0.1265   0.01096   0.00736  -0.0767   0.9592   0.0481
  -4.250  -0.0958   0.00961   0.00588  -0.0782   0.9569   0.0515
  -4.000  -0.0660   0.01000   0.00592  -0.0774   0.9511   0.0565
  -3.750  -0.0583   0.01763   0.01258  -0.0781   0.9561   0.0429
  -3.500  -0.0362   0.01572   0.01039  -0.0770   0.9495   0.0420
  -3.250  -0.0054   0.01440   0.00884  -0.0774   0.9459   0.0422
  -3.000   0.0270   0.01314   0.00740  -0.0782   0.9430   0.0420
  -2.750   0.0538   0.01235   0.00649  -0.0778   0.9373   0.0423
  -2.500   0.0824   0.01164   0.00568  -0.0777   0.9321   0.0427
  -2.250   0.1128   0.01101   0.00499  -0.0780   0.9281   0.0430
  -2.000   0.1383   0.01052   0.00446  -0.0773   0.9211   0.0434
  -1.750   0.1667   0.01014   0.00404  -0.0771   0.9149   0.0440
  -1.500   0.1922   0.00956   0.00342  -0.0764   0.9074   0.0451
  -1.250   0.2185   0.00903   0.00286  -0.0758   0.9002   0.0465
  -1.000   0.2440   0.00870   0.00252  -0.0751   0.8915   0.0486
  -0.750   0.2715   0.00846   0.00226  -0.0747   0.8836   0.0510
  -0.500   0.2967   0.00828   0.00208  -0.0739   0.8743   0.0539
  -0.250   0.3235   0.00812   0.00188  -0.0734   0.8657   0.0580
   0.000   0.3492   0.00782   0.00170  -0.0727   0.8560   0.0905
   0.250   0.3729   0.00738   0.00173  -0.0719   0.8455   0.2448
   0.500   0.3978   0.00711   0.00168  -0.0712   0.8347   0.3297
   0.750   0.4374   0.00554   0.00182  -0.0735   0.8226   0.9694
   1.000   0.5142   0.00559   0.00174  -0.0840   0.7980   1.0000
   1.250   0.5362   0.00564   0.00169  -0.0825   0.7713   1.0000
   1.500   0.5565   0.00577   0.00162  -0.0806   0.7247   1.0000
   1.750   0.5714   0.00617   0.00159  -0.0776   0.6377   1.0000
   2.000   0.5882   0.00661   0.00169  -0.0752   0.5689   1.0000
   2.250   0.6051   0.00708   0.00181  -0.0729   0.4900   1.0000
   2.500   0.6229   0.00757   0.00196  -0.0709   0.4245   1.0000
   2.750   0.6436   0.00790   0.00211  -0.0694   0.3910   1.0000
   3.000   0.6656   0.00817   0.00227  -0.0682   0.3702   1.0000
   3.250   0.6881   0.00840   0.00242  -0.0671   0.3535   1.0000
   3.500   0.7110   0.00862   0.00257  -0.0661   0.3399   1.0000
   3.750   0.7340   0.00883   0.00274  -0.0650   0.3283   1.0000
   4.000   0.7571   0.00904   0.00289  -0.0641   0.3150   1.0000
   4.250   0.7806   0.00923   0.00305  -0.0631   0.3017   1.0000
   4.500   0.8042   0.00941   0.00320  -0.0623   0.2879   1.0000
   4.750   0.8276   0.00962   0.00337  -0.0614   0.2718   1.0000
   5.000   0.8512   0.00983   0.00353  -0.0605   0.2522   1.0000
   5.250   0.8740   0.01011   0.00370  -0.0595   0.2246   1.0000
   5.500   0.8953   0.01054   0.00393  -0.0584   0.1849   1.0000
   5.750   0.9163   0.01103   0.00427  -0.0572   0.1523   1.0000
   6.000   0.9373   0.01154   0.00463  -0.0560   0.1233   1.0000
   6.250   0.9557   0.01235   0.00512  -0.0544   0.0680   1.0000
   6.500   0.9754   0.01307   0.00569  -0.0530   0.0427   1.0000
   6.750   0.9955   0.01376   0.00623  -0.0516   0.0228   1.0000
   7.000   1.0170   0.01432   0.00683  -0.0504   0.0195   1.0000
   7.250   1.0388   0.01483   0.00743  -0.0493   0.0185   1.0000
   7.500   1.0596   0.01543   0.00812  -0.0480   0.0175   1.0000
   7.750   1.0792   0.01614   0.00891  -0.0465   0.0164   1.0000
   8.000   1.0961   0.01710   0.00995  -0.0447   0.0152   1.0000
   8.250   1.1090   0.01842   0.01141  -0.0422   0.0145   1.0000
   8.500   1.1267   0.01922   0.01228  -0.0405   0.0142   1.0000
   8.750   1.1437   0.02009   0.01324  -0.0387   0.0139   1.0000
   9.000   1.1594   0.02107   0.01431  -0.0368   0.0136   1.0000
   9.250   1.1744   0.02214   0.01548  -0.0348   0.0132   1.0000
   9.500   1.1887   0.02333   0.01677  -0.0327   0.0130   1.0000
   9.750   1.2025   0.02463   0.01819  -0.0306   0.0127   1.0000
  10.000   1.2158   0.02605   0.01973  -0.0285   0.0124   1.0000
  10.250   1.2287   0.02746   0.02125  -0.0264   0.0122   1.0000
  10.500   1.2401   0.02892   0.02283  -0.0242   0.0120   1.0000
  10.750   1.2501   0.03031   0.02429  -0.0218   0.0115   1.0000
  11.000   1.2589   0.03195   0.02601  -0.0196   0.0112   1.0000
  11.250   1.2665   0.03389   0.02811  -0.0171   0.0111   1.0000
  11.500   1.2716   0.03594   0.03036  -0.0145   0.0111   1.0000
  11.750   1.2747   0.03825   0.03283  -0.0120   0.0110   1.0000
  12.000   1.2740   0.04028   0.03508  -0.0091   0.0111   1.0000
  12.250   1.2689   0.04287   0.03795  -0.0061   0.0113   1.0000
  12.500   1.2345   0.04875   0.04448  -0.0019   0.0126   1.0000
  12.750   1.2268   0.05139   0.04727  -0.0005   0.0123   1.0000
  13.000   1.1995   0.05731   0.05351   0.0004   0.0131   1.0000
  13.250   1.1787   0.06261   0.05902   0.0000   0.0135   1.0000
  13.500   1.1541   0.06913   0.06572  -0.0019   0.0139   1.0000
  13.750   1.0431   0.07288   0.06982  -0.0053   0.0129   1.0000
  14.000   1.0186   0.08130   0.07841  -0.0096   0.0131   1.0000
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