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GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 685 AIRFOIL (goe685-il)
Reynolds number: 100,000
Max Cl/Cd: 54.21 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe685-il-100000-n5.txt
Download as CSV file: xf-goe685-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 685 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5864   0.06161   0.05594  -0.0691   1.0000   0.0550
 -10.500  -0.6435   0.05479   0.04916  -0.0708   1.0000   0.0543
 -10.250  -0.6888   0.04753   0.04168  -0.0748   1.0000   0.0540
 -10.000  -0.7069   0.04362   0.03750  -0.0749   1.0000   0.0543
  -9.750  -0.7135   0.04060   0.03419  -0.0742   1.0000   0.0549
  -9.500  -0.7033   0.03762   0.03080  -0.0756   0.9973   0.0559
  -9.250  -0.6747   0.03598   0.02916  -0.0778   0.9923   0.0573
  -9.000  -0.6468   0.03426   0.02731  -0.0800   0.9865   0.0586
  -8.750  -0.6168   0.03249   0.02535  -0.0824   0.9815   0.0600
  -8.500  -0.5895   0.03088   0.02350  -0.0840   0.9750   0.0616
  -8.250  -0.5573   0.02933   0.02167  -0.0863   0.9703   0.0637
  -8.000  -0.5306   0.02817   0.02046  -0.0873   0.9632   0.0659
  -7.750  -0.4985   0.02710   0.01933  -0.0892   0.9580   0.0689
  -7.500  -0.4688   0.02605   0.01810  -0.0904   0.9519   0.0719
  -7.250  -0.4390   0.02503   0.01699  -0.0915   0.9453   0.0752
  -7.000  -0.4040   0.02406   0.01594  -0.0936   0.9410   0.0803
  -6.750  -0.3774   0.02321   0.01502  -0.0940   0.9331   0.0867
  -6.500  -0.3443   0.02237   0.01416  -0.0956   0.9275   0.0971
  -6.250  -0.3067   0.02169   0.01351  -0.0979   0.9237   0.1125
  -6.000  -0.2807   0.02130   0.01307  -0.0977   0.9146   0.1277
  -5.750  -0.2454   0.02096   0.01261  -0.0992   0.9091   0.1448
  -5.500  -0.2131   0.02073   0.01230  -0.1000   0.9018   0.1588
  -5.250  -0.1803   0.02052   0.01200  -0.1008   0.8929   0.1713
  -5.000  -0.1477   0.02034   0.01172  -0.1014   0.8839   0.1836
  -4.750  -0.1153   0.02025   0.01153  -0.1020   0.8745   0.1970
  -4.500  -0.0866   0.02032   0.01156  -0.1019   0.8646   0.2083
  -4.250  -0.0549   0.02021   0.01142  -0.1022   0.8568   0.2166
  -4.000  -0.0277   0.01999   0.01107  -0.1019   0.8468   0.2244
  -3.750   0.0039   0.01972   0.01072  -0.1023   0.8390   0.2307
  -3.500   0.0301   0.01955   0.01050  -0.1018   0.8283   0.2369
  -3.250   0.0625   0.01916   0.00993  -0.1023   0.8207   0.2441
  -3.000   0.0881   0.01898   0.00976  -0.1016   0.8090   0.2486
  -2.750   0.1173   0.01873   0.00940  -0.1015   0.7994   0.2550
  -2.500   0.1468   0.01844   0.00902  -0.1015   0.7895   0.2615
  -2.250   0.1743   0.01826   0.00882  -0.1012   0.7783   0.2670
  -2.000   0.2048   0.01799   0.00841  -0.1013   0.7689   0.2740
  -1.750   0.2324   0.01781   0.00819  -0.1009   0.7573   0.2799
  -1.500   0.2605   0.01766   0.00800  -0.1006   0.7462   0.2870
  -1.250   0.2905   0.01748   0.00769  -0.1007   0.7361   0.2948
  -1.000   0.3170   0.01737   0.00759  -0.1001   0.7238   0.3011
  -0.750   0.3449   0.01727   0.00739  -0.0998   0.7121   0.3088
  -0.500   0.3735   0.01715   0.00722  -0.0996   0.7012   0.3158
  -0.250   0.3997   0.01711   0.00716  -0.0991   0.6882   0.3240
   0.000   0.4265   0.01705   0.00708  -0.0986   0.6761   0.3317
   0.250   0.4540   0.01700   0.00698  -0.0983   0.6646   0.3397
   0.500   0.4804   0.01698   0.00693  -0.0977   0.6518   0.3477
   0.750   0.5064   0.01696   0.00693  -0.0972   0.6389   0.3560
   1.000   0.5331   0.01696   0.00689  -0.0967   0.6266   0.3651
   1.250   0.5598   0.01695   0.00686  -0.0962   0.6147   0.3746
   1.500   0.5850   0.01696   0.00689  -0.0955   0.6012   0.3843
   1.750   0.6108   0.01700   0.00692  -0.0949   0.5883   0.3952
   2.000   0.6369   0.01702   0.00694  -0.0944   0.5760   0.4066
   2.250   0.6631   0.01706   0.00697  -0.0938   0.5640   0.4191
   2.500   0.6886   0.01712   0.00707  -0.0933   0.5517   0.4337
   2.750   0.7142   0.01716   0.00716  -0.0927   0.5408   0.4509
   3.000   0.7397   0.01719   0.00726  -0.0921   0.5307   0.4745
   3.250   0.7642   0.01717   0.00745  -0.0914   0.5206   0.5172
   3.750   0.8278   0.01668   0.00783  -0.0925   0.5032   1.0000
   4.000   0.8534   0.01696   0.00799  -0.0919   0.4960   1.0000
   4.250   0.8777   0.01725   0.00826  -0.0912   0.4871   1.0000
   4.500   0.9028   0.01754   0.00846  -0.0906   0.4793   1.0000
   4.750   0.9267   0.01785   0.00878  -0.0898   0.4710   1.0000
   5.000   0.9515   0.01817   0.00904  -0.0891   0.4640   1.0000
   5.250   0.9756   0.01850   0.00938  -0.0884   0.4565   1.0000
   5.500   0.9994   0.01883   0.00970  -0.0876   0.4486   1.0000
   5.750   1.0231   0.01917   0.01003  -0.0868   0.4409   1.0000
   6.000   1.0458   0.01950   0.01040  -0.0858   0.4322   1.0000
   6.250   1.0691   0.01986   0.01074  -0.0849   0.4245   1.0000
   6.500   1.0912   0.02021   0.01116  -0.0839   0.4161   1.0000
   6.750   1.1138   0.02058   0.01153  -0.0829   0.4082   1.0000
   7.000   1.1348   0.02095   0.01199  -0.0818   0.3993   1.0000
   7.250   1.1562   0.02133   0.01237  -0.0806   0.3908   1.0000
   7.500   1.1757   0.02171   0.01284  -0.0792   0.3807   1.0000
   7.750   1.1942   0.02209   0.01329  -0.0776   0.3695   1.0000
   8.000   1.2110   0.02247   0.01369  -0.0757   0.3567   1.0000
   8.250   1.2260   0.02288   0.01412  -0.0736   0.3422   1.0000
   8.500   1.2397   0.02333   0.01462  -0.0714   0.3266   1.0000
   8.750   1.2530   0.02383   0.01519  -0.0691   0.3111   1.0000
   9.000   1.2642   0.02437   0.01576  -0.0665   0.2952   1.0000
   9.250   1.2736   0.02499   0.01640  -0.0638   0.2788   1.0000
   9.500   1.2820   0.02573   0.01713  -0.0610   0.2606   1.0000
   9.750   1.2870   0.02666   0.01800  -0.0580   0.2383   1.0000
  10.000   1.2893   0.02783   0.01908  -0.0550   0.2168   1.0000
  10.250   1.2908   0.02919   0.02036  -0.0521   0.1985   1.0000
  10.500   1.2906   0.03076   0.02186  -0.0494   0.1829   1.0000
  10.750   1.2899   0.03250   0.02358  -0.0469   0.1692   1.0000
  11.000   1.2886   0.03443   0.02550  -0.0447   0.1556   1.0000
  11.250   1.2880   0.03645   0.02756  -0.0428   0.1367   1.0000
  11.500   1.2840   0.03888   0.02995  -0.0411   0.1038   1.0000
  11.750   1.2717   0.04221   0.03311  -0.0396   0.0914   1.0000
  12.000   1.2613   0.04563   0.03646  -0.0385   0.0854   1.0000
  12.250   1.2538   0.04897   0.03985  -0.0378   0.0814   1.0000
  12.500   1.2447   0.05264   0.04358  -0.0374   0.0783   1.0000
  12.750   1.2346   0.05660   0.04758  -0.0372   0.0758   1.0000
  13.000   1.2308   0.05997   0.05107  -0.0372   0.0731   1.0000
  13.250   1.2264   0.06351   0.05473  -0.0373   0.0705   1.0000
  13.500   1.2215   0.06717   0.05847  -0.0375   0.0683   1.0000
  13.750   1.2171   0.07078   0.06210  -0.0377   0.0664   1.0000
  14.000   1.2184   0.07375   0.06517  -0.0378   0.0644   1.0000
  14.250   1.2208   0.07661   0.06815  -0.0379   0.0623   1.0000
  14.500   1.2235   0.07942   0.07104  -0.0380   0.0603   1.0000
  14.750   1.2269   0.08210   0.07374  -0.0381   0.0585   1.0000
  15.000   1.2328   0.08434   0.07596  -0.0378   0.0568   1.0000
  15.250   1.2380   0.08700   0.07878  -0.0380   0.0551   1.0000
  15.500   1.2436   0.08953   0.08143  -0.0382   0.0534   1.0000
  15.750   1.2495   0.09202   0.08399  -0.0383   0.0518   1.0000
  16.000   1.2559   0.09438   0.08636  -0.0384   0.0503   1.0000
  16.250   1.2647   0.09633   0.08830  -0.0382   0.0489   1.0000
  16.500   1.2678   0.09948   0.09165  -0.0389   0.0476   1.0000
  16.750   1.2715   0.10249   0.09482  -0.0395   0.0464   1.0000
  17.000   1.2748   0.10557   0.09802  -0.0403   0.0451   1.0000
  17.250   1.2786   0.10854   0.10107  -0.0411   0.0440   1.0000
  17.500   1.2849   0.11099   0.10355  -0.0416   0.0429   1.0000
  17.750   1.2904   0.11367   0.10627  -0.0422   0.0419   1.0000
  18.000   1.2857   0.11837   0.11122  -0.0442   0.0411   1.0000
  18.250   1.2814   0.12302   0.11610  -0.0463   0.0403   1.0000
  18.500   1.2765   0.12782   0.12109  -0.0486   0.0395   1.0000
  18.750   1.2714   0.13272   0.12617  -0.0511   0.0388   1.0000
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