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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 500,000
Max Cl/Cd: 91.04 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802a-il-500000-n5.txt
Download as CSV file: xf-goe802a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2082   0.10191   0.09955  -0.0473   0.9392   0.0161
  -9.500  -0.2025   0.09903   0.09663  -0.0482   0.9258   0.0161
  -9.250  -0.1964   0.09623   0.09380  -0.0491   0.9138   0.0160
  -9.000  -0.1893   0.09346   0.09102  -0.0502   0.9047   0.0158
  -8.750  -0.1824   0.09050   0.08802  -0.0517   0.8953   0.0159
  -8.250  -0.1671   0.08476   0.08224  -0.0553   0.8781   0.0167
  -8.000  -0.1566   0.08276   0.08020  -0.0567   0.8707   0.0174
  -7.750  -0.1410   0.07961   0.07703  -0.0613   0.8627   0.0195
  -7.500  -0.1251   0.07603   0.07341  -0.0659   0.8552   0.0196
  -7.250  -0.1068   0.07233   0.06965  -0.0710   0.8484   0.0196
  -7.000  -0.0860   0.06852   0.06578  -0.0764   0.8410   0.0197
  -6.750  -0.0622   0.06448   0.06165  -0.0824   0.8342   0.0198
  -6.500  -0.0465   0.06150   0.05865  -0.0838   0.8280   0.0200
  -6.250  -0.0281   0.05931   0.05643  -0.0854   0.8212   0.0204
  -6.000  -0.0063   0.05697   0.05402  -0.0880   0.8145   0.0211
  -5.750   0.0187   0.05419   0.05118  -0.0914   0.8075   0.0224
  -5.500   0.0530   0.05046   0.04729  -0.0970   0.8002   0.0236
  -5.250   0.0832   0.04716   0.04382  -0.1009   0.7935   0.0237
  -5.000   0.1130   0.04402   0.04052  -0.1040   0.7858   0.0238
  -4.750   0.1407   0.04084   0.03715  -0.1064   0.7777   0.0239
  -4.500   0.1617   0.03843   0.03471  -0.1074   0.7687   0.0242
  -4.250   0.1856   0.03653   0.03269  -0.1085   0.7569   0.0245
  -4.000   0.2114   0.03473   0.03078  -0.1096   0.7442   0.0249
  -3.750   0.2381   0.03298   0.02888  -0.1107   0.7322   0.0257
  -3.500   0.2709   0.03137   0.02699  -0.1117   0.7209   0.0282
  -3.250   0.3000   0.02966   0.02503  -0.1125   0.7099   0.0284
  -3.000   0.3280   0.02813   0.02326  -0.1131   0.6976   0.0285
  -2.750   0.3553   0.02658   0.02151  -0.1136   0.6840   0.0285
  -2.250   0.4095   0.02354   0.01807  -0.1144   0.6584   0.0285
  -2.000   0.4347   0.02179   0.01625  -0.1152   0.6445   0.0275
  -1.750   0.4624   0.02060   0.01484  -0.1155   0.6302   0.0271
  -1.500   0.4900   0.01956   0.01358  -0.1157   0.6158   0.0271
  -1.250   0.5175   0.01864   0.01243  -0.1158   0.6017   0.0270
  -1.000   0.5453   0.01779   0.01138  -0.1159   0.5888   0.0275
  -0.750   0.5729   0.01697   0.01035  -0.1160   0.5772   0.0278
  -0.500   0.6001   0.01623   0.00943  -0.1161   0.5655   0.0274
  -0.250   0.6277   0.01547   0.00851  -0.1162   0.5546   0.0273
   0.000   0.6548   0.01474   0.00756  -0.1162   0.5434   0.0274
   0.250   0.6821   0.01368   0.00628  -0.1162   0.5325   0.0279
   0.500   0.7080   0.01259   0.00495  -0.1162   0.5226   0.0285
   0.750   0.7344   0.01208   0.00435  -0.1163   0.5129   0.0291
   1.000   0.7612   0.01205   0.00428  -0.1163   0.5038   0.0301
   1.250   0.7880   0.01187   0.00408  -0.1164   0.4947   0.0310
   1.500   0.8141   0.01170   0.00385  -0.1163   0.4857   0.0315
   1.750   0.8410   0.01158   0.00373  -0.1163   0.4769   0.0321
   2.250   0.8940   0.01157   0.00366  -0.1162   0.4574   0.0337
   2.500   0.9203   0.01168   0.00373  -0.1161   0.4469   0.0349
   2.750   0.9469   0.01177   0.00383  -0.1160   0.4351   0.0367
   3.000   0.9728   0.01190   0.00393  -0.1159   0.4214   0.0393
   3.250   0.9986   0.01218   0.00419  -0.1156   0.4066   0.0450
   3.500   1.0243   0.01240   0.00439  -0.1154   0.3935   0.0560
   3.750   1.0500   0.01259   0.00452  -0.1152   0.3833   0.0646
   4.250   1.1011   0.01300   0.00487  -0.1148   0.3625   0.0732
   4.500   1.1263   0.01322   0.00506  -0.1145   0.3537   0.0783
   5.000   1.1765   0.01356   0.00537  -0.1140   0.3352   0.0862
   5.250   1.2011   0.01371   0.00552  -0.1137   0.3237   0.0863
   5.500   1.2249   0.01393   0.00569  -0.1133   0.3124   0.0864
   5.750   1.2495   0.01409   0.00587  -0.1130   0.3029   0.0865
   6.000   1.2732   0.01432   0.00608  -0.1126   0.2946   0.0865
   6.500   1.3214   0.01462   0.00644  -0.1119   0.2781   0.0867
   6.750   1.3455   0.01478   0.00664  -0.1115   0.2696   0.0869
   7.000   1.3681   0.01505   0.00690  -0.1109   0.2589   0.0872
   7.250   1.3909   0.01530   0.00717  -0.1104   0.2467   0.0874
   7.500   1.4111   0.01575   0.00753  -0.1094   0.2261   0.0877
   7.750   1.4281   0.01642   0.00804  -0.1080   0.1956   0.0878
   8.000   1.4437   0.01716   0.00863  -0.1064   0.1708   0.0879
   8.500   1.4795   0.01818   0.00961  -0.1038   0.1469   0.0882
   8.750   1.4955   0.01872   0.01013  -0.1022   0.1368   0.0883
   9.000   1.5100   0.01917   0.01060  -0.1002   0.1293   0.0886
   9.250   1.5238   0.01977   0.01119  -0.0983   0.1209   0.0888
   9.500   1.5392   0.02035   0.01180  -0.0967   0.1124   0.0891
   9.750   1.5524   0.02110   0.01252  -0.0948   0.1023   0.0892
  10.000   1.5628   0.02204   0.01339  -0.0927   0.0874   0.0893
  10.250   1.5710   0.02315   0.01442  -0.0905   0.0721   0.0894
  10.500   1.5807   0.02419   0.01543  -0.0885   0.0633   0.0896
  10.750   1.5914   0.02519   0.01645  -0.0867   0.0583   0.0902
  11.000   1.6010   0.02629   0.01757  -0.0849   0.0532   0.0906
  11.250   1.6119   0.02733   0.01866  -0.0834   0.0488   0.0907
  11.750   1.6182   0.03073   0.02199  -0.0792   0.0234   0.0910
  12.000   1.6155   0.03304   0.02428  -0.0769   0.0170   0.0913
  12.250   1.6204   0.03479   0.02612  -0.0753   0.0151   0.0916
  12.500   1.6260   0.03652   0.02794  -0.0740   0.0142   0.0921
  12.750   1.6302   0.03843   0.02996  -0.0727   0.0134   0.0924
  13.000   1.6330   0.04055   0.03217  -0.0715   0.0128   0.0926
  13.250   1.6346   0.04286   0.03458  -0.0703   0.0121   0.0931
  13.500   1.6360   0.04524   0.03707  -0.0694   0.0116   0.0938
  13.750   1.6387   0.04757   0.03951  -0.0686   0.0113   0.0946
  14.000   1.6405   0.05009   0.04214  -0.0680   0.0109   0.0955
  14.250   1.6409   0.05284   0.04500  -0.0674   0.0106   0.0963
  14.500   1.6403   0.05580   0.04808  -0.0671   0.0102   0.0967
  14.750   1.6388   0.05899   0.05137  -0.0669   0.0099   0.0972
  15.000   1.6358   0.06243   0.05492  -0.0668   0.0097   0.0980
  15.250   1.6314   0.06613   0.05875  -0.0669   0.0094   0.0989
  15.500   1.6256   0.07013   0.06287  -0.0671   0.0092   0.0993
  15.750   1.6181   0.07445   0.06731  -0.0676   0.0090   0.1001
  16.000   1.6089   0.07907   0.07206  -0.0682   0.0089   0.1012
  16.250   1.5971   0.08418   0.07731  -0.0690   0.0087   0.1018
  16.500   1.5880   0.08898   0.08222  -0.0699   0.0086   0.1028
  16.750   1.5800   0.09367   0.08703  -0.0709   0.0085   0.1042
  17.000   1.5713   0.09851   0.09198  -0.0720   0.0084   0.1057
  17.250   1.5620   0.10353   0.09713  -0.0733   0.0083   0.1078
  17.500   1.5520   0.10873   0.10244  -0.0748   0.0082   0.1103
  17.750   1.5419   0.11402   0.10784  -0.0764   0.0081   0.1121
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