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GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 476 AIRFOIL (goe476-il)
Reynolds number: 100,000
Max Cl/Cd: 49.88 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe476-il-100000-n5.txt
Download as CSV file: xf-goe476-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 476 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2415   0.13181   0.12632  -0.0449   1.0000   0.0851
 -11.500  -0.2483   0.13010   0.12469  -0.0448   1.0000   0.0879
 -11.250  -0.2644   0.12846   0.12312  -0.0458   0.9995   0.0889
 -11.000  -0.2534   0.12405   0.11870  -0.0513   0.9937   0.0891
 -10.750  -0.2411   0.11976   0.11439  -0.0556   0.9871   0.0891
  -9.750  -0.1953   0.09858   0.09308  -0.0715   0.9581   0.0719
  -9.500  -0.1765   0.09500   0.08948  -0.0745   0.9516   0.0714
  -9.250  -0.1636   0.09124   0.08571  -0.0776   0.9417   0.0710
  -9.000  -0.1526   0.08677   0.08122  -0.0822   0.9326   0.0710
  -8.750  -0.1493   0.08064   0.07505  -0.0894   0.9224   0.0718
  -8.500  -0.1440   0.07561   0.06999  -0.0946   0.9099   0.0718
  -8.250  -0.1394   0.07038   0.06471  -0.1003   0.8979   0.0717
  -8.000  -0.1409   0.06446   0.05869  -0.1063   0.8850   0.0717
  -7.750  -0.1687   0.05416   0.04811  -0.1137   0.8679   0.0721
  -7.500  -0.1458   0.05412   0.04807  -0.1131   0.8571   0.0728
  -7.250  -0.1312   0.05108   0.04488  -0.1151   0.8483   0.0738
  -7.000  -0.1326   0.04698   0.04056  -0.1154   0.8354   0.0746
  -6.750  -0.1337   0.04185   0.03503  -0.1158   0.8256   0.0754
  -6.500  -0.1331   0.03771   0.03045  -0.1147   0.8152   0.0764
  -6.250  -0.1258   0.03413   0.02632  -0.1136   0.8070   0.0782
  -6.000  -0.1208   0.03085   0.02230  -0.1113   0.7973   0.0802
  -5.750  -0.0941   0.02991   0.02128  -0.1114   0.7911   0.0813
  -5.500  -0.0760   0.02907   0.02033  -0.1100   0.7820   0.0823
  -5.250  -0.0529   0.02802   0.01908  -0.1094   0.7749   0.0837
  -5.000  -0.0308   0.02701   0.01784  -0.1085   0.7678   0.0855
  -4.750  -0.0106   0.02596   0.01647  -0.1073   0.7597   0.0878
  -4.500   0.0154   0.02496   0.01521  -0.1069   0.7536   0.0900
  -4.250   0.0370   0.02454   0.01477  -0.1058   0.7455   0.0915
  -4.000   0.0617   0.02398   0.01410  -0.1051   0.7386   0.0935
  -3.750   0.0894   0.02331   0.01324  -0.1049   0.7332   0.0961
  -3.500   0.1105   0.02275   0.01248  -0.1036   0.7254   0.0992
  -3.250   0.1361   0.02243   0.01220  -0.1031   0.7192   0.1017
  -3.000   0.1640   0.02206   0.01173  -0.1029   0.7142   0.1050
  -2.750   0.1858   0.02170   0.01129  -0.1017   0.7071   0.1083
  -2.500   0.2116   0.02137   0.01092  -0.1011   0.7014   0.1122
  -2.250   0.2401   0.02112   0.01062  -0.1011   0.6968   0.1171
  -2.000   0.2622   0.02090   0.01032  -0.0998   0.6900   0.1225
  -1.750   0.2869   0.02070   0.01018  -0.0991   0.6841   0.1274
  -1.500   0.3151   0.02047   0.00981  -0.0989   0.6794   0.1355
  -1.250   0.3386   0.02034   0.00976  -0.0980   0.6739   0.1425
  -1.000   0.3621   0.02023   0.00961  -0.0971   0.6680   0.1517
  -0.750   0.3883   0.02006   0.00947  -0.0966   0.6629   0.1612
  -0.500   0.4168   0.01987   0.00925  -0.0966   0.6586   0.1724
  -0.250   0.4371   0.01990   0.00931  -0.0951   0.6519   0.1833
   0.000   0.4617   0.01979   0.00927  -0.0943   0.6464   0.1945
   0.250   0.4898   0.01967   0.00913  -0.0942   0.6420   0.2079
   0.500   0.5140   0.01969   0.00916  -0.0934   0.6370   0.2216
   0.750   0.5365   0.01970   0.00928  -0.0924   0.6312   0.2361
   1.000   0.5637   0.01964   0.00928  -0.0922   0.6262   0.2551
   1.250   0.5949   0.01952   0.00920  -0.0927   0.6221   0.2816
   1.500   0.6173   0.01951   0.00938  -0.0918   0.6162   0.3178
   1.750   0.6385   0.01914   0.00957  -0.0907   0.6105   0.4554
   2.250   0.8036   0.01850   0.00978  -0.1123   0.6015   1.0000
   2.500   0.8191   0.01888   0.01017  -0.1101   0.5956   1.0000
   2.750   0.8397   0.01913   0.01037  -0.1086   0.5902   1.0000
   3.000   0.8647   0.01928   0.01041  -0.1079   0.5854   1.0000
   3.250   0.8837   0.01955   0.01065  -0.1061   0.5795   1.0000
   3.500   0.9006   0.01983   0.01093  -0.1040   0.5726   1.0000
   3.750   0.9247   0.01995   0.01096  -0.1031   0.5672   1.0000
   4.000   0.9444   0.02021   0.01119  -0.1015   0.5617   1.0000
   4.250   0.9596   0.02056   0.01158  -0.0992   0.5552   1.0000
   4.500   0.9821   0.02072   0.01168  -0.0980   0.5498   1.0000
   4.750   1.0034   0.02092   0.01184  -0.0966   0.5444   1.0000
   5.000   1.0160   0.02131   0.01230  -0.0939   0.5376   1.0000
   5.250   1.0374   0.02149   0.01244  -0.0925   0.5321   1.0000
   5.500   1.0576   0.02168   0.01261  -0.0910   0.5265   1.0000
   5.750   1.0686   0.02206   0.01306  -0.0880   0.5190   1.0000
   6.000   1.0908   0.02215   0.01310  -0.0867   0.5129   1.0000
   6.250   1.1027   0.02251   0.01351  -0.0839   0.5059   1.0000
   6.500   1.1172   0.02281   0.01384  -0.0814   0.4993   1.0000
   6.750   1.1413   0.02288   0.01387  -0.0805   0.4939   1.0000
   7.000   1.1460   0.02343   0.01452  -0.0766   0.4864   1.0000
   7.250   1.1623   0.02367   0.01475  -0.0744   0.4798   1.0000
   7.500   1.1751   0.02396   0.01507  -0.0717   0.4731   1.0000
   7.750   1.1805   0.02440   0.01556  -0.0679   0.4653   1.0000
   8.000   1.1994   0.02452   0.01564  -0.0662   0.4581   1.0000
   8.250   1.1997   0.02519   0.01639  -0.0618   0.4494   1.0000
   8.500   1.2188   0.02531   0.01646  -0.0601   0.4413   1.0000
   8.750   1.2177   0.02614   0.01740  -0.0559   0.4315   1.0000
   9.000   1.2321   0.02646   0.01768  -0.0538   0.4224   1.0000
   9.250   1.2335   0.02732   0.01862  -0.0503   0.4114   1.0000
   9.500   1.2388   0.02809   0.01941  -0.0474   0.4000   1.0000
   9.750   1.2474   0.02874   0.02004  -0.0449   0.3882   1.0000
  10.000   1.2454   0.03001   0.02136  -0.0416   0.3740   1.0000
  10.250   1.2445   0.03137   0.02276  -0.0387   0.3594   1.0000
  10.500   1.2438   0.03283   0.02422  -0.0361   0.3433   1.0000
  10.750   1.2434   0.03440   0.02576  -0.0337   0.3264   1.0000
  11.000   1.2432   0.03604   0.02735  -0.0315   0.3092   1.0000
  11.250   1.2438   0.03773   0.02897  -0.0296   0.2937   1.0000
  11.500   1.2446   0.03949   0.03065  -0.0278   0.2799   1.0000
  11.750   1.2460   0.04129   0.03238  -0.0261   0.2680   1.0000
  12.000   1.2482   0.04305   0.03403  -0.0245   0.2577   1.0000
  12.250   1.2511   0.04491   0.03589  -0.0232   0.2482   1.0000
  12.500   1.2554   0.04660   0.03751  -0.0219   0.2400   1.0000
  12.750   1.2586   0.04853   0.03947  -0.0208   0.2316   1.0000
  13.000   1.2643   0.05013   0.04098  -0.0196   0.2245   1.0000
  13.250   1.2678   0.05217   0.04313  -0.0188   0.2172   1.0000
  13.500   1.2731   0.05395   0.04489  -0.0178   0.2106   1.0000
  13.750   1.2793   0.05568   0.04665  -0.0170   0.2048   1.0000
  14.000   1.2831   0.05778   0.04886  -0.0163   0.1985   1.0000
  14.250   1.2889   0.05957   0.05064  -0.0156   0.1927   1.0000
  14.500   1.2924   0.06177   0.05293  -0.0151   0.1869   1.0000
  14.750   1.2946   0.06413   0.05539  -0.0146   0.1808   1.0000
  15.000   1.2987   0.06618   0.05740  -0.0141   0.1752   1.0000
  15.250   1.2982   0.06903   0.06045  -0.0139   0.1687   1.0000
  15.500   1.2993   0.07160   0.06307  -0.0137   0.1630   1.0000
  15.750   1.3000   0.07431   0.06586  -0.0136   0.1572   1.0000
  16.000   1.2991   0.07727   0.06893  -0.0137   0.1511   1.0000
  16.250   1.2988   0.08013   0.07179  -0.0137   0.1456   1.0000
  16.500   1.2965   0.08342   0.07522  -0.0140   0.1393   1.0000
  16.750   1.2947   0.08654   0.07832  -0.0142   0.1339   1.0000
  17.000   1.2920   0.08999   0.08191  -0.0147   0.1279   1.0000
  17.250   1.2897   0.09331   0.08526  -0.0151   0.1229   1.0000
  17.500   1.2880   0.09659   0.08858  -0.0156   0.1181   1.0000
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