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GOE 29B AIRFOIL (goe29b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 29B AIRFOIL (goe29b-il)
Reynolds number: 100,000
Max Cl/Cd: 52.82 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe29b-il-100000.txt
Download as CSV file: xf-goe29b-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 29B 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1973   0.10531   0.10083  -0.0270   1.0000   0.0644
  -7.750  -0.2136   0.10577   0.10145  -0.0247   1.0000   0.0646
  -7.500  -0.2408   0.10688   0.10274  -0.0194   1.0000   0.0647
  -7.250  -0.2265   0.10664   0.10252  -0.0321   0.9874   0.0651
  -7.000  -0.1994   0.09944   0.09534  -0.0318   0.9833   0.0657
  -6.750  -0.1690   0.09400   0.08988  -0.0347   0.9759   0.0668
  -6.500  -0.1319   0.08929   0.08514  -0.0420   0.9683   0.0687
  -6.250  -0.0964   0.08529   0.08111  -0.0503   0.9559   0.0715
  -5.750  -0.0221   0.07843   0.07410  -0.0721   0.9249   0.0749
  -5.500  -0.0029   0.07439   0.07006  -0.0715   0.9117   0.0760
  -5.250   0.0182   0.07134   0.06698  -0.0732   0.8967   0.0777
  -5.000   0.0396   0.06870   0.06428  -0.0758   0.8812   0.0798
  -4.750   0.0652   0.06638   0.06184  -0.0803   0.8662   0.0827
  -4.500   0.1048   0.06454   0.05975  -0.0904   0.8507   0.0853
  -4.250   0.1132   0.06119   0.05646  -0.0873   0.8367   0.0865
  -4.000   0.1293   0.05872   0.05397  -0.0868   0.8234   0.0887
  -3.750   0.1532   0.05649   0.05163  -0.0887   0.8114   0.0923
  -3.500   0.2010   0.05519   0.04993  -0.0977   0.7985   0.0974
  -3.250   0.2136   0.05190   0.04671  -0.0961   0.7856   0.0987
  -3.000   0.2332   0.04957   0.04434  -0.0959   0.7743   0.1014
  -2.750   0.2624   0.04772   0.04231  -0.0979   0.7636   0.1070
  -2.500   0.2975   0.04581   0.04017  -0.1017   0.7512   0.1121
  -2.250   0.3175   0.04356   0.03789  -0.1013   0.7405   0.1162
  -2.000   0.3541   0.04221   0.03621  -0.1043   0.7293   0.1265
  -1.750   0.3745   0.04001   0.03403  -0.1039   0.7171   0.1312
  -1.500   0.4083   0.03867   0.03239  -0.1060   0.7065   0.1421
  -1.250   0.4329   0.03691   0.03055  -0.1060   0.6959   0.1503
  -1.000   0.4614   0.03538   0.02889  -0.1070   0.6852   0.1613
  -0.750   0.4904   0.03396   0.02725  -0.1077   0.6768   0.1766
  -0.500   0.5197   0.03318   0.02630  -0.1087   0.6656   0.2041
  -0.250   0.5435   0.03144   0.02452  -0.1085   0.6572   0.2284
   0.000   0.5674   0.03008   0.02315  -0.1086   0.6468   0.2738
   0.250   0.5908   0.02862   0.02166  -0.1081   0.6381   0.3251
   0.500   0.6167   0.02741   0.02037  -0.1080   0.6281   0.3723
   0.750   0.6449   0.02642   0.01926  -0.1080   0.6190   0.4041
   1.000   0.6755   0.02551   0.01821  -0.1084   0.6103   0.4224
   1.250   0.7131   0.02510   0.01745  -0.1098   0.6027   0.3840
   1.500   0.7648   0.02588   0.01719  -0.1106   0.5941   0.1812
   1.750   0.7962   0.02530   0.01624  -0.1102   0.5875   0.1646
   2.000   0.8252   0.02503   0.01576  -0.1098   0.5781   0.1531
   2.250   0.8545   0.02456   0.01504  -0.1093   0.5713   0.1536
   2.500   0.8812   0.02437   0.01482  -0.1089   0.5614   0.1545
   2.750   0.9097   0.02386   0.01413  -0.1083   0.5540   0.1563
   3.000   0.9352   0.02361   0.01401  -0.1078   0.5434   0.1627
   3.250   0.9630   0.02327   0.01351  -0.1071   0.5355   0.1665
   3.500   0.9883   0.02310   0.01340  -0.1064   0.5244   0.1734
   3.750   1.0148   0.02294   0.01319  -0.1057   0.5146   0.1821
   4.000   1.0420   0.02272   0.01291  -0.1051   0.5045   0.1912
   4.250   1.0677   0.02272   0.01293  -0.1045   0.4923   0.2090
   4.500   1.0947   0.02263   0.01286  -0.1040   0.4807   0.2415
   4.750   1.1197   0.02147   0.01265  -0.1028   0.4699   1.0000
   5.000   1.1444   0.02182   0.01281  -0.1019   0.4557   1.0000
   5.250   1.1689   0.02224   0.01308  -0.1011   0.4417   1.0000
   5.500   1.1937   0.02269   0.01339  -0.1004   0.4287   1.0000
   5.750   1.2201   0.02310   0.01355  -0.0999   0.4178   1.0000
   6.000   1.2433   0.02369   0.01414  -0.0992   0.4056   1.0000
   6.250   1.2672   0.02434   0.01475  -0.0986   0.3954   1.0000
   6.500   1.2928   0.02479   0.01505  -0.0981   0.3867   1.0000
   6.750   1.3148   0.02542   0.01576  -0.0973   0.3766   1.0000
   7.000   1.3411   0.02575   0.01587  -0.0969   0.3688   1.0000
   7.250   1.3615   0.02641   0.01671  -0.0960   0.3594   1.0000
   7.500   1.3876   0.02680   0.01694  -0.0956   0.3529   1.0000
   7.750   1.4078   0.02761   0.01792  -0.0947   0.3455   1.0000
   8.000   1.4318   0.02815   0.01844  -0.0942   0.3393   1.0000
   8.250   1.4554   0.02885   0.01914  -0.0936   0.3338   1.0000
   8.500   1.4752   0.02969   0.02014  -0.0927   0.3275   1.0000
   8.750   1.5002   0.03022   0.02059  -0.0923   0.3222   1.0000
   9.000   1.5203   0.03115   0.02166  -0.0915   0.3167   1.0000
   9.250   1.5396   0.03198   0.02262  -0.0905   0.3106   1.0000
   9.500   1.5669   0.03244   0.02291  -0.0903   0.3053   1.0000
   9.750   1.5804   0.03365   0.02440  -0.0888   0.2989   1.0000
  10.000   1.6017   0.03434   0.02511  -0.0880   0.2928   1.0000
  10.250   1.6236   0.03524   0.02601  -0.0874   0.2872   1.0000
  10.500   1.6359   0.03651   0.02751  -0.0857   0.2809   1.0000
  10.750   1.6629   0.03716   0.02804  -0.0856   0.2752   1.0000
  11.000   1.6724   0.03873   0.02987  -0.0837   0.2691   1.0000
  11.250   1.6883   0.03972   0.03092  -0.0824   0.2624   1.0000
  11.500   1.7087   0.04073   0.03188  -0.0817   0.2557   1.0000
  11.750   1.7118   0.04222   0.03362  -0.0792   0.2492   1.0000
  12.000   1.7433   0.04264   0.03378  -0.0797   0.2417   1.0000
  12.250   1.7353   0.04463   0.03616  -0.0760   0.2368   1.0000
  12.500   1.7442   0.04578   0.03740  -0.0742   0.2310   1.0000
  12.750   1.7702   0.04665   0.03815  -0.0742   0.2252   1.0000
  13.000   1.7540   0.04889   0.04074  -0.0699   0.2217   1.0000
  13.250   1.7446   0.05091   0.04298  -0.0666   0.2178   1.0000
  13.500   1.7939   0.05032   0.04206  -0.0686   0.2105   1.0000
  13.750   1.7676   0.05315   0.04526  -0.0640   0.2085   1.0000
  14.000   1.7423   0.05661   0.04904  -0.0609   0.2062   1.0000
  14.250   1.7182   0.06058   0.05329  -0.0589   0.2038   1.0000
  14.500   1.7005   0.06440   0.05731  -0.0577   0.2011   1.0000
  14.750   1.7625   0.06094   0.05356  -0.0575   0.1945   1.0000
  15.000   1.7249   0.06655   0.05953  -0.0561   0.1933   1.0000
  15.250   1.6760   0.07445   0.06776  -0.0562   0.1928   1.0000
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