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GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 655 AIRFOIL (goe655-il)
Reynolds number: 100,000
Max Cl/Cd: 49.03 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe655-il-100000-n5.txt
Download as CSV file: xf-goe655-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 655 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3436   0.09301   0.08809  -0.0471   1.0000   0.0480
  -9.750  -0.3598   0.08845   0.08361  -0.0477   1.0000   0.0481
  -9.500  -0.3761   0.08453   0.07978  -0.0475   1.0000   0.0481
  -9.250  -0.3958   0.08077   0.07612  -0.0470   1.0000   0.0479
  -9.000  -0.4223   0.07698   0.07244  -0.0461   1.0000   0.0477
  -8.750  -0.4501   0.06017   0.05539  -0.0662   0.9839   0.0472
  -8.500  -0.4653   0.04971   0.04426  -0.0753   0.9680   0.0477
  -8.250  -0.4566   0.04369   0.03755  -0.0795   0.9586   0.0488
  -8.000  -0.4363   0.04176   0.03555  -0.0801   0.9493   0.0499
  -7.750  -0.4082   0.03918   0.03270  -0.0826   0.9440   0.0510
  -7.500  -0.3907   0.03666   0.02983  -0.0827   0.9336   0.0519
  -7.250  -0.3611   0.03419   0.02694  -0.0847   0.9285   0.0536
  -7.000  -0.3412   0.03224   0.02458  -0.0843   0.9183   0.0553
  -6.750  -0.3096   0.03021   0.02202  -0.0857   0.9131   0.0568
  -6.500  -0.2851   0.02863   0.02027  -0.0855   0.9042   0.0578
  -6.250  -0.2532   0.02728   0.01882  -0.0866   0.8982   0.0592
  -6.000  -0.2243   0.02626   0.01768  -0.0870   0.8907   0.0612
  -5.750  -0.1950   0.02525   0.01648  -0.0873   0.8829   0.0637
  -5.500  -0.1632   0.02419   0.01522  -0.0880   0.8762   0.0657
  -5.250  -0.1356   0.02327   0.01416  -0.0877   0.8670   0.0673
  -5.000  -0.1057   0.02230   0.01321  -0.0881   0.8589   0.0695
  -4.750  -0.0758   0.02152   0.01239  -0.0882   0.8485   0.0730
  -4.500  -0.0483   0.02083   0.01159  -0.0878   0.8355   0.0769
  -4.250  -0.0202   0.02006   0.01078  -0.0875   0.8230   0.0806
  -4.000   0.0097   0.01938   0.01004  -0.0875   0.8116   0.0854
  -3.750   0.0372   0.01883   0.00942  -0.0872   0.7997   0.0923
  -3.500   0.0634   0.01832   0.00891  -0.0867   0.7881   0.1025
  -3.250   0.0920   0.01778   0.00838  -0.0866   0.7777   0.1189
  -3.000   0.1194   0.01723   0.00798  -0.0863   0.7665   0.1525
  -2.750   0.1452   0.01681   0.00771  -0.0858   0.7544   0.2021
  -2.500   0.1727   0.01647   0.00749  -0.0856   0.7431   0.2538
  -2.250   0.2008   0.01621   0.00728  -0.0853   0.7316   0.3010
  -2.000   0.2259   0.01602   0.00716  -0.0846   0.7185   0.3433
  -1.750   0.2515   0.01582   0.00706  -0.0839   0.7059   0.3931
  -1.500   0.2772   0.01558   0.00696  -0.0832   0.6937   0.4542
  -1.250   0.3028   0.01535   0.00686  -0.0824   0.6810   0.5122
  -1.000   0.3272   0.01514   0.00679  -0.0814   0.6671   0.5671
  -0.750   0.3508   0.01489   0.00675  -0.0801   0.6531   0.6411
  -0.500   0.3771   0.01462   0.00675  -0.0789   0.6387   0.7528
  -0.250   0.4366   0.01447   0.00671  -0.0843   0.6213   0.8990
   0.000   0.4954   0.01452   0.00656  -0.0903   0.6032   0.9794
   0.250   0.5311   0.01466   0.00649  -0.0919   0.5868   1.0000
   0.500   0.5522   0.01480   0.00644  -0.0905   0.5716   1.0000
   0.750   0.5734   0.01497   0.00642  -0.0891   0.5565   1.0000
   1.000   0.5947   0.01516   0.00643  -0.0878   0.5418   1.0000
   1.250   0.6162   0.01537   0.00645  -0.0865   0.5279   1.0000
   1.500   0.6380   0.01559   0.00651  -0.0852   0.5149   1.0000
   1.750   0.6597   0.01583   0.00661  -0.0840   0.5022   1.0000
   2.000   0.6819   0.01608   0.00673  -0.0829   0.4910   1.0000
   2.250   0.7044   0.01635   0.00685  -0.0818   0.4809   1.0000
   2.500   0.7267   0.01662   0.00703  -0.0807   0.4704   1.0000
   2.750   0.7494   0.01691   0.00720  -0.0797   0.4613   1.0000
   3.000   0.7717   0.01720   0.00739  -0.0787   0.4516   1.0000
   3.250   0.7942   0.01750   0.00760  -0.0776   0.4425   1.0000
   3.500   0.8167   0.01781   0.00781  -0.0766   0.4340   1.0000
   3.750   0.8390   0.01812   0.00806  -0.0757   0.4254   1.0000
   4.000   0.8614   0.01844   0.00829  -0.0747   0.4175   1.0000
   4.250   0.8835   0.01876   0.00858  -0.0737   0.4094   1.0000
   4.500   0.9058   0.01909   0.00883  -0.0727   0.4021   1.0000
   4.750   0.9281   0.01944   0.00914  -0.0717   0.3950   1.0000
   5.000   0.9498   0.01977   0.00946  -0.0707   0.3877   1.0000
   5.250   0.9719   0.02013   0.00974  -0.0697   0.3811   1.0000
   5.500   0.9934   0.02049   0.01013  -0.0687   0.3743   1.0000
   5.750   1.0157   0.02086   0.01047  -0.0678   0.3687   1.0000
   6.000   1.0378   0.02126   0.01086  -0.0669   0.3634   1.0000
   6.250   1.0591   0.02165   0.01130  -0.0659   0.3576   1.0000
   6.500   1.0808   0.02205   0.01169  -0.0649   0.3523   1.0000
   6.750   1.1017   0.02247   0.01213  -0.0639   0.3466   1.0000
   7.000   1.1213   0.02289   0.01262  -0.0627   0.3404   1.0000
   7.250   1.1418   0.02331   0.01301  -0.0615   0.3347   1.0000
   7.500   1.1605   0.02377   0.01354  -0.0602   0.3285   1.0000
   7.750   1.1785   0.02422   0.01406  -0.0587   0.3221   1.0000
   8.000   1.1984   0.02468   0.01447  -0.0576   0.3169   1.0000
   8.250   1.2142   0.02519   0.01514  -0.0558   0.3103   1.0000
   8.500   1.2306   0.02568   0.01568  -0.0542   0.3042   1.0000
   8.750   1.2468   0.02618   0.01619  -0.0525   0.2986   1.0000
   9.000   1.2586   0.02674   0.01689  -0.0502   0.2917   1.0000
   9.250   1.2721   0.02727   0.01745  -0.0481   0.2856   1.0000
   9.500   1.2830   0.02791   0.01820  -0.0458   0.2787   1.0000
   9.750   1.2941   0.02855   0.01890  -0.0436   0.2721   1.0000
  10.000   1.3052   0.02925   0.01965  -0.0415   0.2658   1.0000
  10.250   1.3149   0.03003   0.02055  -0.0394   0.2590   1.0000
  10.500   1.3266   0.03077   0.02130  -0.0376   0.2541   1.0000
  10.750   1.3356   0.03174   0.02243  -0.0356   0.2477   1.0000
  11.000   1.3453   0.03266   0.02341  -0.0338   0.2426   1.0000
  11.250   1.3556   0.03360   0.02439  -0.0321   0.2382   1.0000
  11.500   1.3635   0.03477   0.02572  -0.0304   0.2330   1.0000
  11.750   1.3720   0.03588   0.02690  -0.0288   0.2287   1.0000
  12.000   1.3816   0.03696   0.02799  -0.0274   0.2250   1.0000
  12.250   1.3868   0.03844   0.02964  -0.0258   0.2205   1.0000
  12.500   1.3925   0.03985   0.03115  -0.0244   0.2163   1.0000
  12.750   1.3995   0.04113   0.03244  -0.0231   0.2125   1.0000
  13.000   1.4015   0.04296   0.03443  -0.0218   0.2083   1.0000
  13.250   1.4019   0.04491   0.03650  -0.0206   0.2036   1.0000
  13.500   1.4053   0.04659   0.03820  -0.0196   0.1993   1.0000
  13.750   1.4045   0.04884   0.04057  -0.0188   0.1952   1.0000
  14.000   1.4011   0.05143   0.04331  -0.0181   0.1909   1.0000
  14.250   1.4012   0.05369   0.04564  -0.0176   0.1870   1.0000
  14.500   1.4024   0.05592   0.04789  -0.0171   0.1830   1.0000
  14.750   1.3947   0.05936   0.05155  -0.0171   0.1795   1.0000
  15.000   1.3889   0.06265   0.05499  -0.0172   0.1759   1.0000
  15.250   1.3883   0.06538   0.05778  -0.0173   0.1724   1.0000
  15.500   1.3888   0.06803   0.06047  -0.0174   0.1687   1.0000
  15.750   1.3746   0.07286   0.06554  -0.0184   0.1660   1.0000
  16.000   1.3612   0.07777   0.07064  -0.0196   0.1629   1.0000
  16.250   1.3535   0.08195   0.07495  -0.0207   0.1596   1.0000
  16.500   1.3640   0.08327   0.07621  -0.0206   0.1553   1.0000
  16.750   1.3394   0.09037   0.08358  -0.0232   0.1532   1.0000
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