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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 200,000
Max Cl/Cd: 64.83 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe488-il-200000-n5.txt
Download as CSV file: xf-goe488-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4291   0.09649   0.09282  -0.0270   1.0000   0.0214
  -9.000  -0.4344   0.09220   0.08860  -0.0291   1.0000   0.0223
  -8.750  -0.4351   0.08917   0.08560  -0.0292   1.0000   0.0226
  -8.500  -0.4237   0.08849   0.08494  -0.0275   1.0000   0.0238
  -8.250  -0.4229   0.08627   0.08275  -0.0273   1.0000   0.0247
  -8.000  -0.4295   0.08349   0.08003  -0.0271   1.0000   0.0248
  -7.750  -0.4400   0.08087   0.07749  -0.0264   1.0000   0.0249
  -7.500  -0.4455   0.07787   0.07454  -0.0268   1.0000   0.0252
  -7.250  -0.4511   0.07478   0.07148  -0.0270   1.0000   0.0253
  -7.000  -0.4557   0.07161   0.06833  -0.0272   1.0000   0.0256
  -6.750  -0.4509   0.06792   0.06462  -0.0294   0.9989   0.0268
  -6.500  -0.4245   0.06127   0.05780  -0.0381   0.9940   0.0287
  -6.250  -0.3979   0.05366   0.04996  -0.0460   0.9886   0.0298
  -6.000  -0.3716   0.04464   0.04054  -0.0531   0.9834   0.0320
  -5.750  -0.3483   0.04323   0.03907  -0.0545   0.9799   0.0335
  -5.500  -0.3203   0.03986   0.03549  -0.0572   0.9770   0.0345
  -5.250  -0.2967   0.03539   0.03070  -0.0589   0.9718   0.0352
  -5.000  -0.2689   0.03216   0.02715  -0.0607   0.9687   0.0369
  -4.750  -0.2428   0.02843   0.02297  -0.0617   0.9646   0.0381
  -4.500  -0.2156   0.02519   0.01922  -0.0624   0.9602   0.0386
  -4.000  -0.1551   0.02107   0.01429  -0.0641   0.9518   0.0397
  -3.750  -0.1214   0.01971   0.01262  -0.0653   0.9480   0.0406
  -3.500  -0.0853   0.01863   0.01125  -0.0670   0.9449   0.0416
  -3.250  -0.0575   0.01760   0.01001  -0.0669   0.9386   0.0417
  -3.000  -0.0240   0.01658   0.00880  -0.0680   0.9351   0.0418
  -2.750   0.0058   0.01575   0.00784  -0.0682   0.9300   0.0419
  -2.500   0.0357   0.01502   0.00700  -0.0685   0.9246   0.0422
  -2.250   0.0695   0.01432   0.00623  -0.0696   0.9208   0.0426
  -2.000   0.0956   0.01383   0.00569  -0.0691   0.9134   0.0431
  -1.750   0.1266   0.01312   0.00498  -0.0696   0.9083   0.0443
  -1.500   0.1537   0.01262   0.00449  -0.0693   0.9010   0.0461
  -1.250   0.1839   0.01223   0.00410  -0.0696   0.8941   0.0484
  -1.000   0.2116   0.01195   0.00380  -0.0693   0.8858   0.0507
  -0.750   0.2420   0.01167   0.00349  -0.0696   0.8782   0.0537
  -0.500   0.2688   0.01146   0.00327  -0.0691   0.8678   0.0582
  -0.250   0.2968   0.01117   0.00303  -0.0689   0.8562   0.0705
   0.000   0.3236   0.01075   0.00287  -0.0685   0.8444   0.1275
   0.250   0.3505   0.01044   0.00281  -0.0682   0.8336   0.2131
   0.500   0.3764   0.01024   0.00275  -0.0677   0.8216   0.2720
   1.000   0.4827   0.00844   0.00273  -0.0778   0.7915   1.0000
   1.500   0.5305   0.00854   0.00263  -0.0756   0.7430   1.0000
   1.750   0.5539   0.00863   0.00257  -0.0743   0.7021   1.0000
   2.000   0.5750   0.00887   0.00248  -0.0724   0.6426   1.0000
   2.250   0.5933   0.00929   0.00252  -0.0702   0.5766   1.0000
   2.500   0.6096   0.00985   0.00265  -0.0677   0.4928   1.0000
   2.750   0.6259   0.01045   0.00283  -0.0655   0.4234   1.0000
   3.000   0.6458   0.01088   0.00304  -0.0639   0.3877   1.0000
   3.250   0.6672   0.01122   0.00324  -0.0626   0.3648   1.0000
   3.500   0.6893   0.01153   0.00347  -0.0615   0.3476   1.0000
   3.750   0.7124   0.01179   0.00368  -0.0605   0.3353   1.0000
   4.000   0.7357   0.01203   0.00392  -0.0596   0.3253   1.0000
   4.250   0.7589   0.01230   0.00416  -0.0587   0.3155   1.0000
   4.500   0.7826   0.01254   0.00443  -0.0578   0.3055   1.0000
   4.750   0.8062   0.01278   0.00470  -0.0570   0.2953   1.0000
   5.000   0.8294   0.01305   0.00496  -0.0561   0.2792   1.0000
   5.250   0.8517   0.01338   0.00521  -0.0551   0.2485   1.0000
   5.500   0.8732   0.01379   0.00545  -0.0540   0.2080   1.0000
   5.750   0.8936   0.01436   0.00580  -0.0528   0.1672   1.0000
   6.000   0.9139   0.01500   0.00625  -0.0517   0.1333   1.0000
   6.250   0.9351   0.01557   0.00673  -0.0506   0.1084   1.0000
   6.500   0.9533   0.01650   0.00739  -0.0492   0.0603   1.0000
   6.750   0.9730   0.01727   0.00810  -0.0478   0.0381   1.0000
   7.000   0.9921   0.01812   0.00885  -0.0464   0.0219   1.0000
   7.250   1.0125   0.01882   0.00962  -0.0451   0.0195   1.0000
   7.500   1.0318   0.01963   0.01053  -0.0437   0.0171   1.0000
   7.750   1.0496   0.02060   0.01169  -0.0420   0.0151   1.0000
   8.000   1.0672   0.02152   0.01276  -0.0404   0.0145   1.0000
   8.250   1.0842   0.02243   0.01383  -0.0387   0.0140   1.0000
   8.500   1.0995   0.02347   0.01501  -0.0367   0.0135   1.0000
   8.750   1.1136   0.02459   0.01627  -0.0347   0.0131   1.0000
   9.000   1.1268   0.02578   0.01759  -0.0325   0.0125   1.0000
   9.250   1.1400   0.02693   0.01886  -0.0305   0.0118   1.0000
   9.500   1.1516   0.02822   0.02025  -0.0283   0.0111   1.0000
   9.750   1.1606   0.02962   0.02180  -0.0258   0.0106   1.0000
  10.000   1.1686   0.03114   0.02343  -0.0232   0.0103   1.0000
  10.250   1.1753   0.03289   0.02530  -0.0206   0.0101   1.0000
  10.500   1.1813   0.03490   0.02744  -0.0181   0.0098   1.0000
  10.750   1.1866   0.03727   0.02997  -0.0158   0.0096   1.0000
  11.000   1.1910   0.03992   0.03280  -0.0136   0.0095   1.0000
  11.250   1.1928   0.04255   0.03564  -0.0113   0.0094   1.0000
  11.500   1.1925   0.04477   0.03810  -0.0090   0.0093   1.0000
  11.750   1.1898   0.04723   0.04080  -0.0069   0.0092   1.0000
  12.000   1.1849   0.04998   0.04377  -0.0051   0.0092   1.0000
  12.250   1.1773   0.05307   0.04711  -0.0038   0.0091   1.0000
  12.500   1.1684   0.05654   0.05080  -0.0031   0.0091   1.0000
  12.750   1.1585   0.06025   0.05473  -0.0030   0.0091   1.0000
  13.000   1.1461   0.06467   0.05937  -0.0038   0.0091   1.0000
  13.250   1.1319   0.06975   0.06466  -0.0055   0.0091   1.0000
  13.500   1.1173   0.07533   0.07046  -0.0083   0.0090   1.0000
  13.750   1.1025   0.08155   0.07686  -0.0117   0.0091   1.0000
  14.000   1.0860   0.08866   0.08415  -0.0160   0.0091   1.0000
  14.250   1.0692   0.09636   0.09200  -0.0207   0.0092   1.0000
  14.500   1.0518   0.10468   0.10047  -0.0260   0.0092   1.0000
  14.750   1.0351   0.11319   0.10912  -0.0314   0.0093   1.0000
  15.000   1.0180   0.12211   0.11815  -0.0368   0.0093   1.0000
  15.250   0.8501   0.12694   0.12356  -0.0380   0.0101   1.0000
  15.500   0.8001   0.14319   0.14005  -0.0482   0.0107   1.0000
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