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GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 414 AIRFOIL (goe414-il)
Reynolds number: 200,000
Max Cl/Cd: 72.95 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe414-il-200000-n5.txt
Download as CSV file: xf-goe414-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 414 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3950   0.04398   0.04027  -0.1178   0.9488   0.0190
  -9.750  -0.4080   0.03676   0.03245  -0.1226   0.9364   0.0193
  -9.500  -0.4043   0.03283   0.02797  -0.1233   0.9280   0.0199
  -9.250  -0.3909   0.03006   0.02483  -0.1236   0.9218   0.0206
  -9.000  -0.3714   0.02850   0.02312  -0.1237   0.9168   0.0214
  -8.750  -0.3531   0.02729   0.02175  -0.1231   0.9101   0.0224
  -8.500  -0.3300   0.02597   0.02019  -0.1233   0.9056   0.0239
  -8.250  -0.3099   0.02468   0.01858  -0.1227   0.8989   0.0255
  -8.000  -0.2866   0.02352   0.01709  -0.1224   0.8927   0.0267
  -7.750  -0.2655   0.02188   0.01530  -0.1219   0.8867   0.0283
  -7.500  -0.2425   0.02104   0.01435  -0.1215   0.8792   0.0302
  -7.250  -0.2166   0.02016   0.01328  -0.1214   0.8737   0.0324
  -7.000  -0.1932   0.01938   0.01229  -0.1207   0.8660   0.0342
  -6.750  -0.1672   0.01841   0.01114  -0.1206   0.8608   0.0363
  -6.500  -0.1439   0.01774   0.01041  -0.1200   0.8527   0.0387
  -6.250  -0.1167   0.01710   0.00963  -0.1200   0.8465   0.0411
  -6.000  -0.0919   0.01660   0.00899  -0.1194   0.8382   0.0436
  -5.750  -0.0648   0.01601   0.00831  -0.1194   0.8319   0.0466
  -5.500  -0.0396   0.01559   0.00783  -0.1189   0.8234   0.0496
  -5.250  -0.0118   0.01518   0.00729  -0.1189   0.8163   0.0542
  -5.000   0.0140   0.01486   0.00698  -0.1185   0.8066   0.0611
  -4.750   0.0410   0.01455   0.00661  -0.1183   0.7979   0.0702
  -4.500   0.0682   0.01430   0.00625  -0.1181   0.7885   0.0807
  -4.250   0.0948   0.01412   0.00598  -0.1178   0.7787   0.0899
  -4.000   0.1222   0.01391   0.00570  -0.1177   0.7703   0.0979
  -3.750   0.1490   0.01378   0.00547  -0.1175   0.7608   0.1060
  -3.500   0.1757   0.01360   0.00525  -0.1174   0.7515   0.1140
  -3.250   0.2030   0.01346   0.00499  -0.1172   0.7420   0.1204
  -3.000   0.2294   0.01329   0.00479  -0.1169   0.7313   0.1265
  -2.750   0.2562   0.01316   0.00459  -0.1167   0.7211   0.1346
  -2.500   0.2829   0.01301   0.00439  -0.1165   0.7111   0.1432
  -2.250   0.3094   0.01288   0.00422  -0.1163   0.7008   0.1555
  -2.000   0.3358   0.01273   0.00408  -0.1161   0.6910   0.1736
  -1.750   0.3623   0.01259   0.00396  -0.1159   0.6816   0.1998
  -1.500   0.3883   0.01246   0.00390  -0.1157   0.6718   0.2367
  -1.250   0.4146   0.01238   0.00386  -0.1154   0.6625   0.2760
  -1.000   0.4408   0.01233   0.00382  -0.1152   0.6534   0.3100
  -0.750   0.4669   0.01229   0.00380  -0.1149   0.6439   0.3403
  -0.500   0.4929   0.01227   0.00377  -0.1146   0.6347   0.3700
  -0.250   0.5185   0.01222   0.00377  -0.1143   0.6251   0.4029
   0.250   0.5675   0.01194   0.00381  -0.1132   0.6069   0.5321
   0.500   0.6076   0.01116   0.00403  -0.1151   0.5972   0.9258
   0.750   0.6540   0.01129   0.00405  -0.1193   0.5871   1.0000
   1.000   0.6778   0.01143   0.00409  -0.1185   0.5775   1.0000
   1.250   0.7017   0.01157   0.00414  -0.1178   0.5677   1.0000
   1.500   0.7255   0.01173   0.00420  -0.1171   0.5582   1.0000
   1.750   0.7492   0.01189   0.00428  -0.1164   0.5480   1.0000
   2.000   0.7730   0.01205   0.00437  -0.1157   0.5379   1.0000
   2.250   0.7965   0.01223   0.00447  -0.1149   0.5282   1.0000
   2.500   0.8199   0.01241   0.00458  -0.1142   0.5180   1.0000
   2.750   0.8434   0.01261   0.00471  -0.1135   0.5081   1.0000
   3.000   0.8666   0.01282   0.00484  -0.1127   0.4992   1.0000
   3.250   0.8901   0.01303   0.00500  -0.1120   0.4906   1.0000
   3.500   0.9135   0.01326   0.00516  -0.1113   0.4836   1.0000
   3.750   0.9373   0.01348   0.00535  -0.1107   0.4769   1.0000
   4.000   0.9608   0.01373   0.00555  -0.1100   0.4713   1.0000
   4.250   0.9849   0.01396   0.00577  -0.1095   0.4656   1.0000
   4.500   1.0087   0.01421   0.00600  -0.1089   0.4604   1.0000
   4.750   1.0326   0.01448   0.00624  -0.1083   0.4561   1.0000
   5.000   1.0570   0.01471   0.00651  -0.1079   0.4516   1.0000
   5.250   1.0808   0.01498   0.00678  -0.1074   0.4469   1.0000
   5.500   1.1044   0.01527   0.00706  -0.1068   0.4424   1.0000
   5.750   1.1281   0.01554   0.00737  -0.1062   0.4377   1.0000
   6.000   1.1517   0.01581   0.00769  -0.1057   0.4332   1.0000
   6.250   1.1753   0.01611   0.00801  -0.1051   0.4293   1.0000
   6.500   1.1977   0.01643   0.00835  -0.1044   0.4236   1.0000
   6.750   1.2169   0.01673   0.00869  -0.1030   0.4140   1.0000
   7.000   1.2344   0.01706   0.00904  -0.1014   0.4025   1.0000
   7.250   1.2516   0.01742   0.00940  -0.0997   0.3923   1.0000
   7.500   1.2673   0.01774   0.00979  -0.0977   0.3819   1.0000
   7.750   1.2834   0.01808   0.01020  -0.0958   0.3717   1.0000
   8.000   1.2962   0.01849   0.01065  -0.0935   0.3556   1.0000
   8.250   1.3065   0.01903   0.01116  -0.0908   0.3316   1.0000
   8.500   1.3131   0.01981   0.01183  -0.0877   0.2946   1.0000
   8.750   1.3078   0.02133   0.01304  -0.0833   0.2477   1.0000
   9.000   1.3014   0.02322   0.01466  -0.0792   0.2076   1.0000
   9.250   1.2870   0.02581   0.01686  -0.0745   0.1349   1.0000
   9.500   1.2705   0.02878   0.01950  -0.0702   0.0867   1.0000
   9.750   1.2523   0.03213   0.02254  -0.0662   0.0309   1.0000
  10.000   1.2536   0.03415   0.02460  -0.0642   0.0241   1.0000
  10.250   1.2573   0.03605   0.02659  -0.0625   0.0216   1.0000
  10.500   1.2607   0.03803   0.02868  -0.0610   0.0201   1.0000
  10.750   1.2654   0.03997   0.03075  -0.0597   0.0190   1.0000
  11.000   1.2684   0.04213   0.03305  -0.0585   0.0179   1.0000
  11.250   1.2700   0.04450   0.03555  -0.0574   0.0170   1.0000
  11.500   1.2696   0.04717   0.03835  -0.0563   0.0162   1.0000
  11.750   1.2674   0.05016   0.04147  -0.0554   0.0156   1.0000
  12.000   1.2630   0.05350   0.04498  -0.0547   0.0152   1.0000
  12.250   1.2563   0.05722   0.04885  -0.0541   0.0148   1.0000
  12.500   1.2520   0.06076   0.05251  -0.0537   0.0145   1.0000
  12.750   1.2491   0.06420   0.05609  -0.0534   0.0143   1.0000
  13.000   1.2458   0.06775   0.05976  -0.0532   0.0140   1.0000
  13.250   1.2424   0.07136   0.06348  -0.0531   0.0137   1.0000
  13.500   1.2393   0.07500   0.06723  -0.0531   0.0134   1.0000
  13.750   1.2363   0.07864   0.07098  -0.0532   0.0130   1.0000
  14.000   1.2339   0.08223   0.07466  -0.0533   0.0125   1.0000
  14.250   1.2317   0.08579   0.07830  -0.0535   0.0121   1.0000
  14.500   1.2301   0.08927   0.08186  -0.0536   0.0118   1.0000
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