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GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 477 AIRFOIL (goe477-il)
Reynolds number: 100,000
Max Cl/Cd: 56.67 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe477-il-100000.txt
Download as CSV file: xf-goe477-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 477 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4043   0.10434   0.10017  -0.0201   1.0000   0.0906
  -7.500  -0.4245   0.10344   0.09935  -0.0183   1.0000   0.0910
  -7.250  -0.4487   0.10258   0.09857  -0.0198   1.0000   0.0917
  -7.000  -0.4629   0.10049   0.09648  -0.0247   1.0000   0.0923
  -6.750  -0.4572   0.09569   0.09176  -0.0182   1.0000   0.0940
  -6.500  -0.4519   0.09320   0.08928  -0.0140   1.0000   0.0965
  -6.250  -0.4534   0.09077   0.08687  -0.0132   1.0000   0.0992
  -6.000  -0.4324   0.08593   0.08173  -0.0343   0.9936   0.1070
  -5.750  -0.4240   0.08103   0.07698  -0.0302   0.9913   0.1086
  -5.500  -0.4105   0.07823   0.07421  -0.0280   0.9883   0.1118
  -5.250  -0.3824   0.07308   0.06874  -0.0412   0.9839   0.1228
  -5.000  -0.3736   0.07044   0.06624  -0.0367   0.9810   0.1260
  -4.750  -0.3489   0.06639   0.06192  -0.0440   0.9762   0.1385
  -4.500  -0.3334   0.06374   0.05936  -0.0422   0.9733   0.1430
  -4.250  -0.3056   0.05999   0.05540  -0.0473   0.9699   0.1558
  -4.000  -0.2853   0.05722   0.05242  -0.0498   0.9653   0.1699
  -3.750  -0.2631   0.05472   0.04982  -0.0512   0.9614   0.1856
  -3.500  -0.2368   0.05208   0.04707  -0.0530   0.9582   0.2018
  -3.250  -0.1729   0.04090   0.03419  -0.0628   0.9559   0.1230
  -3.000  -0.1514   0.03821   0.03132  -0.0625   0.9515   0.1183
  -2.750  -0.1207   0.03558   0.02816  -0.0635   0.9473   0.1177
  -2.500  -0.0779   0.03347   0.02542  -0.0662   0.9423   0.1194
  -2.250  -0.0496   0.03205   0.02357  -0.0664   0.9339   0.1240
  -1.750   0.0309   0.03026   0.02125  -0.0705   0.9154   0.1360
  -1.500   0.0696   0.02939   0.02025  -0.0724   0.9082   0.1410
  -1.250   0.0993   0.02902   0.01981  -0.0728   0.9005   0.1487
  -1.000   0.1431   0.02847   0.01920  -0.0755   0.8949   0.1565
  -0.750   0.1658   0.02819   0.01890  -0.0746   0.8857   0.1638
  -0.500   0.2135   0.02775   0.01852  -0.0778   0.8801   0.1814
  -0.250   0.2345   0.02747   0.01834  -0.0765   0.8696   0.1981
   0.000   0.2734   0.02667   0.01792  -0.0781   0.8616   0.2604
   0.250   0.3533   0.02415   0.01723  -0.0868   0.8535   1.0000
   0.500   0.3922   0.02403   0.01689  -0.0881   0.8419   1.0000
   0.750   0.4572   0.02336   0.01603  -0.0936   0.8352   1.0000
   1.000   0.4843   0.02335   0.01592  -0.0929   0.8233   1.0000
   1.250   0.5230   0.02310   0.01558  -0.0941   0.8145   1.0000
   1.500   0.5668   0.02258   0.01499  -0.0958   0.8065   1.0000
   1.750   0.5947   0.02242   0.01478  -0.0950   0.7950   1.0000
   2.000   0.6452   0.02152   0.01383  -0.0975   0.7894   1.0000
   2.250   0.6701   0.02126   0.01355  -0.0961   0.7763   1.0000
   2.500   0.6973   0.02086   0.01315  -0.0949   0.7633   1.0000
   2.750   0.7263   0.02034   0.01262  -0.0939   0.7503   1.0000
   3.000   0.7561   0.01968   0.01198  -0.0930   0.7365   1.0000
   3.250   0.7846   0.01896   0.01127  -0.0917   0.7204   1.0000
   3.500   0.8139   0.01813   0.01044  -0.0905   0.7022   1.0000
   3.750   0.8379   0.01747   0.00981  -0.0886   0.6771   1.0000
   4.000   0.8670   0.01672   0.00899  -0.0874   0.6453   1.0000
   4.250   0.8966   0.01621   0.00825  -0.0863   0.6017   1.0000
   4.500   0.9220   0.01627   0.00792  -0.0849   0.5512   1.0000
   4.750   0.9432   0.01677   0.00805  -0.0833   0.5075   1.0000
   5.000   0.9647   0.01745   0.00838  -0.0819   0.4754   1.0000
   5.250   0.9872   0.01819   0.00891  -0.0809   0.4506   1.0000
   5.500   1.0122   0.01899   0.00950  -0.0805   0.4319   1.0000
   5.750   1.0374   0.01978   0.01016  -0.0801   0.4165   1.0000
   6.000   1.0619   0.02052   0.01087  -0.0796   0.4034   1.0000
   6.250   1.0866   0.02128   0.01163  -0.0792   0.3923   1.0000
   6.500   1.1139   0.02209   0.01237  -0.0792   0.3833   1.0000
   6.750   1.1372   0.02281   0.01323  -0.0786   0.3749   1.0000
   7.000   1.1647   0.02364   0.01401  -0.0787   0.3679   1.0000
   7.250   1.1848   0.02424   0.01479  -0.0775   0.3583   1.0000
   7.500   1.2043   0.02478   0.01538  -0.0762   0.3470   1.0000
   7.750   1.2235   0.02522   0.01582  -0.0749   0.3352   1.0000
   8.000   1.2424   0.02561   0.01620  -0.0735   0.3237   1.0000
   8.250   1.2570   0.02600   0.01681  -0.0714   0.3129   1.0000
   8.500   1.2722   0.02637   0.01728  -0.0694   0.3019   1.0000
   8.750   1.2842   0.02662   0.01760  -0.0669   0.2893   1.0000
   9.000   1.2935   0.02686   0.01792  -0.0639   0.2763   1.0000
   9.250   1.2952   0.02707   0.01826  -0.0598   0.2609   1.0000
   9.500   1.2907   0.02734   0.01869  -0.0547   0.2439   1.0000
   9.750   1.2846   0.02789   0.01933  -0.0499   0.2215   1.0000
  10.000   1.2820   0.02881   0.02027  -0.0460   0.1832   1.0000
  10.250   1.2724   0.03106   0.02187  -0.0424   0.0990   1.0000
  10.500   1.2663   0.03370   0.02423  -0.0393   0.0820   1.0000
  10.750   1.2635   0.03607   0.02662  -0.0367   0.0751   1.0000
  11.000   1.2600   0.03848   0.02915  -0.0343   0.0703   1.0000
  11.250   1.2520   0.04128   0.03202  -0.0320   0.0673   1.0000
  11.500   1.2488   0.04378   0.03467  -0.0301   0.0650   1.0000
  11.750   1.2465   0.04630   0.03735  -0.0284   0.0631   1.0000
  12.000   1.2446   0.04890   0.04005  -0.0269   0.0614   1.0000
  12.250   1.2443   0.05144   0.04268  -0.0255   0.0597   1.0000
  12.500   1.2470   0.05388   0.04507  -0.0240   0.0572   1.0000
  12.750   1.2679   0.05534   0.04643  -0.0225   0.0546   1.0000
  13.000   1.2890   0.05684   0.04804  -0.0213   0.0529   1.0000
  13.250   1.3180   0.05840   0.04971  -0.0204   0.0516   1.0000
  13.500   1.3421   0.06052   0.05200  -0.0196   0.0503   1.0000
  13.750   1.3603   0.06302   0.05462  -0.0190   0.0485   1.0000
  14.000   1.3824   0.06605   0.05777  -0.0186   0.0469   1.0000
  14.250   1.3913   0.06947   0.06143  -0.0177   0.0468   1.0000
  14.500   1.3883   0.07300   0.06525  -0.0167   0.0469   1.0000
  14.750   1.3795   0.07672   0.06928  -0.0158   0.0472   1.0000
  15.000   1.3661   0.08081   0.07368  -0.0152   0.0476   1.0000
  15.250   1.3439   0.08555   0.07875  -0.0154   0.0480   1.0000
  15.500   1.3194   0.09090   0.08442  -0.0163   0.0484   1.0000
  15.750   1.2923   0.09698   0.09081  -0.0183   0.0490   1.0000
  16.000   1.2654   0.10373   0.09784  -0.0213   0.0496   1.0000
  16.250   1.2371   0.11147   0.10584  -0.0254   0.0501   1.0000
  16.500   1.2070   0.12037   0.11498  -0.0309   0.0507   1.0000
  16.750   1.1757   0.13049   0.12531  -0.0376   0.0516   1.0000
  17.000   1.1416   0.14231   0.13730  -0.0457   0.0526   1.0000
  17.250   1.1081   0.15534   0.15043  -0.0544   0.0539   1.0000
  17.500   1.0948   0.16430   0.15939  -0.0590   0.0552   1.0000
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