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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 500,000
Max Cl/Cd: 90.95 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802b-il-500000-n5.txt
Download as CSV file: xf-goe802b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2020   0.09994   0.09754  -0.0475   0.9264   0.0151
  -9.250  -0.1959   0.09705   0.09462  -0.0486   0.9145   0.0151
  -9.000  -0.1893   0.09411   0.09165  -0.0499   0.9052   0.0153
  -8.750  -0.1835   0.09071   0.08823  -0.0519   0.8954   0.0163
  -8.500  -0.1737   0.08876   0.08625  -0.0527   0.8876   0.0168
  -8.250  -0.1630   0.08655   0.08403  -0.0544   0.8790   0.0190
  -8.000  -0.1554   0.08349   0.08093  -0.0571   0.8706   0.0193
  -7.750  -0.1422   0.08005   0.07746  -0.0612   0.8630   0.0193
  -7.500  -0.1270   0.07650   0.07387  -0.0657   0.8552   0.0194
  -7.250  -0.1092   0.07281   0.07013  -0.0707   0.8485   0.0194
  -7.000  -0.0874   0.06873   0.06598  -0.0770   0.8413   0.0195
  -6.750  -0.0730   0.06576   0.06298  -0.0784   0.8346   0.0198
  -6.500  -0.0555   0.06350   0.06069  -0.0801   0.8283   0.0201
  -6.250  -0.0347   0.06108   0.05823  -0.0829   0.8212   0.0208
  -6.000  -0.0115   0.05826   0.05534  -0.0864   0.8143   0.0219
  -5.750   0.0212   0.05444   0.05139  -0.0926   0.8078   0.0233
  -5.500   0.0511   0.05091   0.04773  -0.0973   0.8004   0.0234
  -5.250   0.0806   0.04756   0.04420  -0.1011   0.7932   0.0235
  -5.000   0.1107   0.04434   0.04082  -0.1044   0.7860   0.0236
  -4.750   0.1311   0.04135   0.03778  -0.1057   0.7777   0.0238
  -4.500   0.1540   0.03932   0.03567  -0.1068   0.7683   0.0241
  -4.250   0.1789   0.03744   0.03368  -0.1081   0.7564   0.0245
  -4.000   0.2053   0.03558   0.03168  -0.1094   0.7441   0.0252
  -3.750   0.2327   0.03372   0.02966  -0.1106   0.7320   0.0263
  -3.500   0.2679   0.03182   0.02743  -0.1120   0.7206   0.0281
  -3.250   0.2965   0.03007   0.02545  -0.1128   0.7093   0.0283
  -3.000   0.3240   0.02835   0.02352  -0.1134   0.6974   0.0283
  -2.750   0.3513   0.02664   0.02162  -0.1140   0.6854   0.0283
  -2.500   0.3784   0.02503   0.01980  -0.1145   0.6720   0.0283
  -2.250   0.4032   0.02320   0.01788  -0.1152   0.6572   0.0275
  -2.000   0.4308   0.02187   0.01635  -0.1156   0.6429   0.0271
  -1.750   0.4588   0.02069   0.01495  -0.1159   0.6298   0.0270
  -1.500   0.4865   0.01965   0.01368  -0.1161   0.6166   0.0269
  -1.250   0.5146   0.01867   0.01249  -0.1162   0.6033   0.0275
  -1.000   0.5422   0.01777   0.01138  -0.1163   0.5902   0.0275
  -0.750   0.5695   0.01696   0.01035  -0.1164   0.5768   0.0271
  -0.500   0.5972   0.01612   0.00932  -0.1165   0.5640   0.0270
  -0.250   0.6248   0.01527   0.00826  -0.1165   0.5534   0.0271
   0.000   0.6523   0.01417   0.00691  -0.1165   0.5429   0.0276
   0.250   0.6790   0.01289   0.00534  -0.1166   0.5337   0.0282
   0.500   0.7053   0.01221   0.00453  -0.1167   0.5238   0.0288
   0.750   0.7323   0.01209   0.00437  -0.1167   0.5146   0.0296
   1.000   0.7590   0.01193   0.00416  -0.1167   0.5042   0.0304
   1.250   0.7855   0.01174   0.00392  -0.1167   0.4946   0.0308
   1.500   0.8121   0.01164   0.00378  -0.1166   0.4843   0.0313
   1.750   0.8389   0.01160   0.00371  -0.1166   0.4757   0.0320
   2.000   0.8657   0.01159   0.00368  -0.1166   0.4664   0.0328
   2.250   0.8923   0.01163   0.00368  -0.1165   0.4578   0.0336
   2.500   0.9192   0.01172   0.00377  -0.1164   0.4480   0.0350
   2.750   0.9454   0.01184   0.00387  -0.1163   0.4361   0.0368
   3.000   0.9711   0.01200   0.00399  -0.1160   0.4212   0.0405
   3.250   0.9974   0.01228   0.00428  -0.1158   0.4064   0.0468
   3.500   1.0231   0.01246   0.00442  -0.1156   0.3940   0.0603
   3.750   1.0484   0.01271   0.00461  -0.1154   0.3828   0.0671
   4.000   1.0744   0.01286   0.00475  -0.1152   0.3737   0.0709
   4.500   1.1249   0.01331   0.00512  -0.1146   0.3502   0.0799
   4.750   1.1498   0.01353   0.00530  -0.1143   0.3378   0.0864
   5.000   1.1743   0.01373   0.00547  -0.1140   0.3278   0.0868
   5.250   1.1994   0.01385   0.00561  -0.1137   0.3212   0.0869
   5.500   1.2244   0.01400   0.00577  -0.1135   0.3141   0.0870
   6.000   1.2735   0.01423   0.00605  -0.1129   0.3003   0.0871
   6.250   1.2973   0.01441   0.00624  -0.1125   0.2903   0.0873
   6.500   1.3213   0.01458   0.00643  -0.1121   0.2811   0.0875
   6.750   1.3446   0.01481   0.00666  -0.1116   0.2711   0.0878
   7.000   1.3679   0.01504   0.00691  -0.1111   0.2606   0.0881
   7.250   1.3898   0.01537   0.00722  -0.1104   0.2470   0.0882
   7.500   1.4099   0.01583   0.00759  -0.1094   0.2248   0.0883
   7.750   1.4260   0.01657   0.00813  -0.1079   0.1921   0.0884
   8.000   1.4419   0.01725   0.00869  -0.1063   0.1675   0.0886
   8.250   1.4598   0.01777   0.00919  -0.1050   0.1539   0.0889
   8.500   1.4773   0.01829   0.00968  -0.1036   0.1437   0.0891
   8.750   1.4941   0.01878   0.01017  -0.1021   0.1345   0.0894
   9.000   1.5073   0.01930   0.01069  -0.0999   0.1267   0.0897
   9.250   1.5219   0.01986   0.01125  -0.0981   0.1179   0.0898
   9.750   1.5500   0.02122   0.01261  -0.0947   0.0987   0.0901
  10.000   1.5633   0.02198   0.01335  -0.0929   0.0882   0.0905
  10.250   1.5720   0.02306   0.01436  -0.0907   0.0737   0.0912
  10.500   1.5812   0.02413   0.01539  -0.0886   0.0651   0.0915
  10.750   1.5907   0.02521   0.01648  -0.0867   0.0583   0.0918
  11.000   1.6015   0.02622   0.01753  -0.0851   0.0531   0.0922
  11.250   1.6090   0.02752   0.01883  -0.0832   0.0476   0.0928
  11.500   1.6194   0.02862   0.01999  -0.0817   0.0431   0.0933
  11.750   1.6195   0.03059   0.02189  -0.0794   0.0252   0.0935
  12.000   1.6156   0.03300   0.02426  -0.0769   0.0170   0.0939
  12.250   1.6206   0.03473   0.02608  -0.0754   0.0153   0.0946
  12.500   1.6248   0.03659   0.02803  -0.0739   0.0143   0.0955
  12.750   1.6279   0.03862   0.03015  -0.0726   0.0133   0.0960
  13.000   1.6319   0.04063   0.03226  -0.0714   0.0126   0.0976
  13.250   1.6363   0.04265   0.03438  -0.0704   0.0122   0.0994
  13.750   1.6411   0.04727   0.03922  -0.0687   0.0112   0.1031
  14.000   1.6417   0.04991   0.04197  -0.0680   0.0108   0.1050
  14.250   1.6411   0.05278   0.04494  -0.0674   0.0105   0.1083
  14.500   1.6391   0.05592   0.04819  -0.0671   0.0102   0.1130
  14.750   1.6355   0.05938   0.05176  -0.0668   0.0099   0.1157
  15.000   1.6298   0.06320   0.05570  -0.0668   0.0096   0.1176
  15.250   1.6238   0.06715   0.05977  -0.0669   0.0094   0.1192
  15.500   1.6204   0.07085   0.06359  -0.0672   0.0093   0.1209
  15.750   1.6155   0.07482   0.06768  -0.0676   0.0091   0.1223
  16.000   1.6095   0.07899   0.07197  -0.0681   0.0090   0.1236
  16.250   1.6024   0.08339   0.07650  -0.0688   0.0089   0.1249
  16.500   1.5946   0.08797   0.08120  -0.0696   0.0087   0.1271
  17.000   1.5767   0.09765   0.09114  -0.0718   0.0085   0.1617
  17.250   1.5677   0.10269   0.09645  -0.0732   0.0083   0.3888
  17.750   1.5486   0.11224   0.10706  -0.0760   0.0081   1.0000
  18.000   1.5384   0.11757   0.11251  -0.0777   0.0080   1.0000
  18.250   1.5280   0.12300   0.11804  -0.0796   0.0078   1.0000
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