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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 100,000
Max Cl/Cd: 58.62 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe178-il-100000-n5.txt
Download as CSV file: xf-goe178-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3693   0.10795   0.10315  -0.0157   1.0000   0.0536
  -8.500  -0.3726   0.10585   0.10113  -0.0203   1.0000   0.0545
  -8.250  -0.3737   0.10316   0.09853  -0.0238   1.0000   0.0548
  -8.000  -0.3712   0.09990   0.09533  -0.0275   1.0000   0.0549
  -7.750  -0.3566   0.09460   0.09003  -0.0228   1.0000   0.0561
  -7.500  -0.3482   0.09138   0.08683  -0.0224   1.0000   0.0573
  -7.250  -0.3421   0.08856   0.08406  -0.0228   1.0000   0.0593
  -7.000  -0.3367   0.08576   0.08129  -0.0255   1.0000   0.0631
  -6.750  -0.3307   0.08260   0.07820  -0.0367   1.0000   0.0659
  -6.500  -0.3211   0.07870   0.07429  -0.0419   1.0000   0.0661
  -6.000  -0.3130   0.06662   0.06223  -0.0418   1.0000   0.0456
  -5.750  -0.3007   0.06209   0.05763  -0.0450   1.0000   0.0437
  -5.000  -0.1842   0.04220   0.03687  -0.0710   0.9770   0.0454
  -4.750  -0.1497   0.04073   0.03532  -0.0741   0.9679   0.0485
  -4.500  -0.1090   0.03536   0.02947  -0.0799   0.9582   0.0489
  -4.250  -0.0694   0.03063   0.02414  -0.0844   0.9480   0.0489
  -4.000  -0.0328   0.02733   0.02030  -0.0873   0.9353   0.0499
  -3.750   0.0010   0.02496   0.01740  -0.0889   0.9191   0.0525
  -3.500   0.0333   0.02281   0.01477  -0.0899   0.9003   0.0531
  -3.250   0.0663   0.02104   0.01257  -0.0908   0.8807   0.0536
  -3.000   0.0988   0.01963   0.01077  -0.0913   0.8598   0.0544
  -2.750   0.1298   0.01853   0.00943  -0.0915   0.8372   0.0555
  -2.500   0.1589   0.01780   0.00855  -0.0913   0.8127   0.0570
  -2.250   0.1868   0.01722   0.00778  -0.0909   0.7867   0.0591
  -2.000   0.2139   0.01676   0.00713  -0.0903   0.7591   0.0625
  -1.750   0.2407   0.01640   0.00659  -0.0897   0.7305   0.0678
  -1.500   0.2675   0.01608   0.00614  -0.0892   0.7025   0.0736
  -1.250   0.2947   0.01571   0.00559  -0.0887   0.6769   0.0813
  -1.000   0.3217   0.01545   0.00516  -0.0883   0.6541   0.0951
  -0.750   0.3488   0.01525   0.00485  -0.0879   0.6334   0.1125
  -0.500   0.3758   0.01515   0.00468  -0.0877   0.6154   0.1364
  -0.250   0.4030   0.01510   0.00456  -0.0874   0.6001   0.1561
   0.000   0.4306   0.01503   0.00449  -0.0873   0.5870   0.1991
   0.250   0.4579   0.01454   0.00453  -0.0876   0.5761   0.3797
   0.750   0.5080   0.01343   0.00446  -0.0855   0.5566   1.0000
   1.000   0.5357   0.01367   0.00448  -0.0854   0.5484   1.0000
   1.250   0.5635   0.01389   0.00456  -0.0854   0.5403   1.0000
   1.500   0.5912   0.01414   0.00465  -0.0853   0.5333   1.0000
   1.750   0.6188   0.01438   0.00477  -0.0852   0.5254   1.0000
   2.000   0.6463   0.01464   0.00490  -0.0851   0.5176   1.0000
   2.250   0.6735   0.01488   0.00504  -0.0849   0.5083   1.0000
   2.500   0.7007   0.01512   0.00521  -0.0848   0.4990   1.0000
   2.750   0.7278   0.01539   0.00537  -0.0846   0.4913   1.0000
   3.000   0.7552   0.01564   0.00563  -0.0845   0.4841   1.0000
   3.250   0.7825   0.01593   0.00587  -0.0844   0.4781   1.0000
   3.500   0.8097   0.01622   0.00615  -0.0843   0.4722   1.0000
   3.750   0.8369   0.01650   0.00647  -0.0842   0.4657   1.0000
   4.000   0.8639   0.01682   0.00674  -0.0841   0.4602   1.0000
   4.250   0.8909   0.01711   0.00713  -0.0840   0.4533   1.0000
   4.500   0.9178   0.01743   0.00747  -0.0838   0.4474   1.0000
   4.750   0.9444   0.01774   0.00787  -0.0836   0.4404   1.0000
   5.000   0.9707   0.01803   0.00819  -0.0834   0.4322   1.0000
   5.250   0.9966   0.01831   0.00856  -0.0831   0.4222   1.0000
   5.500   1.0224   0.01858   0.00890  -0.0827   0.4126   1.0000
   5.750   1.0481   0.01885   0.00928  -0.0824   0.4028   1.0000
   6.000   1.0738   0.01915   0.00973  -0.0821   0.3935   1.0000
   6.250   1.0993   0.01945   0.01012  -0.0817   0.3853   1.0000
   6.500   1.1238   0.01966   0.01047  -0.0811   0.3708   1.0000
   6.750   1.1478   0.01982   0.01079  -0.0805   0.3490   1.0000
   7.000   1.1716   0.02006   0.01113  -0.0799   0.3287   1.0000
   7.250   1.1952   0.02039   0.01157  -0.0793   0.3046   1.0000
   7.500   1.2133   0.02110   0.01200  -0.0780   0.2490   1.0000
   7.750   1.2294   0.02238   0.01301  -0.0768   0.1928   1.0000
   8.000   1.2278   0.02584   0.01547  -0.0742   0.0615   1.0000
   8.250   1.2395   0.02765   0.01736  -0.0723   0.0439   1.0000
   8.500   1.2528   0.02914   0.01895  -0.0707   0.0338   1.0000
   8.750   1.2657   0.03055   0.02054  -0.0690   0.0294   1.0000
   9.250   1.2815   0.03388   0.02421  -0.0650   0.0256   1.0000
   9.500   1.2839   0.03563   0.02616  -0.0624   0.0241   1.0000
   9.750   1.2838   0.03760   0.02828  -0.0601   0.0229   1.0000
  10.000   1.2816   0.03992   0.03074  -0.0582   0.0218   1.0000
  10.250   1.2769   0.04274   0.03371  -0.0569   0.0210   1.0000
  10.500   1.2705   0.04606   0.03717  -0.0562   0.0205   1.0000
  10.750   1.2638   0.04966   0.04089  -0.0559   0.0201   1.0000
  11.000   1.2603   0.05300   0.04434  -0.0555   0.0198   1.0000
  11.250   1.2603   0.05595   0.04742  -0.0549   0.0196   1.0000
  11.500   1.2628   0.05855   0.05011  -0.0539   0.0192   1.0000
  11.750   1.2684   0.06076   0.05242  -0.0524   0.0189   1.0000
  12.000   1.2762   0.06283   0.05460  -0.0508   0.0184   1.0000
  12.250   1.2834   0.06513   0.05709  -0.0495   0.0178   1.0000
  12.500   1.2890   0.06775   0.05988  -0.0486   0.0171   1.0000
  12.750   1.2926   0.07069   0.06299  -0.0480   0.0165   1.0000
  13.000   1.2950   0.07387   0.06635  -0.0476   0.0160   1.0000
  13.250   1.2963   0.07731   0.06999  -0.0472   0.0158   1.0000
  13.500   1.2953   0.08114   0.07404  -0.0473   0.0156   1.0000
  13.750   1.2914   0.08541   0.07853  -0.0478   0.0155   1.0000
  14.000   1.2847   0.09010   0.08346  -0.0488   0.0154   1.0000
  14.250   1.2756   0.09524   0.08884  -0.0503   0.0154   1.0000
  14.500   1.2647   0.10078   0.09461  -0.0523   0.0154   1.0000
  14.750   1.2522   0.10679   0.10084  -0.0549   0.0154   1.0000
  15.000   1.2383   0.11330   0.10758  -0.0581   0.0154   1.0000
  15.250   1.2228   0.12047   0.11497  -0.0620   0.0155   1.0000
  15.500   1.2061   0.12828   0.12301  -0.0666   0.0156   1.0000
  15.750   1.1885   0.13684   0.13178  -0.0720   0.0158   1.0000
  16.000   1.1697   0.14643   0.14156  -0.0783   0.0160   1.0000
  16.250   1.1494   0.15739   0.15268  -0.0857   0.0162   1.0000
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