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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.09 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802a-il-1000000.txt
Download as CSV file: xf-goe802a-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2732   0.11168   0.11012  -0.0235   1.0000   0.0162
 -10.500  -0.2727   0.10796   0.10641  -0.0252   1.0000   0.0163
 -10.250  -0.2708   0.10423   0.10269  -0.0268   1.0000   0.0163
 -10.000  -0.2675   0.10059   0.09906  -0.0281   1.0000   0.0163
  -9.750  -0.2604   0.09654   0.09502  -0.0277   1.0000   0.0165
  -9.500  -0.2540   0.09344   0.09193  -0.0284   1.0000   0.0166
  -9.250  -0.2460   0.09021   0.08872  -0.0297   0.9943   0.0168
  -9.000  -0.2355   0.08667   0.08516  -0.0320   0.9815   0.0170
  -8.750  -0.2277   0.08337   0.08186  -0.0335   0.9665   0.0173
  -8.500  -0.2241   0.08044   0.07890  -0.0340   0.9496   0.0177
  -8.250  -0.2217   0.07746   0.07589  -0.0344   0.9344   0.0181
  -8.000  -0.2192   0.07426   0.07265  -0.0352   0.9213   0.0187
  -7.750  -0.2177   0.07062   0.06897  -0.0372   0.9084   0.0196
  -7.500  -0.2182   0.06688   0.06519  -0.0402   0.8956   0.0197
  -7.250  -0.2131   0.06240   0.06067  -0.0454   0.8845   0.0198
  -7.000  -0.2505   0.06961   0.06780  -0.0498   0.9029   0.0197
  -6.750  -0.2307   0.06517   0.06326  -0.0553   0.8922   0.0198
  -6.500  -0.2109   0.06109   0.05907  -0.0593   0.8817   0.0198
  -6.250  -0.1896   0.05705   0.05493  -0.0627   0.8720   0.0199
  -6.000  -0.1749   0.05190   0.04966  -0.0653   0.8624   0.0201
  -5.750  -0.1561   0.04945   0.04715  -0.0663   0.8528   0.0203
  -5.250  -0.1129   0.04472   0.04226  -0.0689   0.8336   0.0208
  -5.000  -0.0893   0.04232   0.03973  -0.0702   0.8245   0.0213
  -4.750  -0.0643   0.03977   0.03708  -0.0716   0.8158   0.0220
  -4.250  -0.0045   0.03400   0.03078  -0.0737   0.7983   0.0239
  -4.000   0.0180   0.02984   0.02636  -0.0745   0.7891   0.0242
  -3.750   0.0423   0.02818   0.02463  -0.0749   0.7788   0.0245
  -3.500   0.0674   0.02682   0.02316  -0.0752   0.7683   0.0249
  -3.250   0.0932   0.02550   0.02172  -0.0754   0.7558   0.0254
  -3.000   0.1198   0.02417   0.02024  -0.0756   0.7423   0.0264
  -2.750   0.1505   0.02353   0.01927  -0.0749   0.7277   0.0285
  -2.500   0.1760   0.02069   0.01613  -0.0750   0.7124   0.0290
  -2.250   0.2023   0.01961   0.01493  -0.0752   0.6944   0.0293
  -2.000   0.2291   0.01878   0.01396  -0.0753   0.6752   0.0297
  -1.750   0.2562   0.01806   0.01310  -0.0753   0.6558   0.0305
  -1.500   0.2838   0.01736   0.01222  -0.0753   0.6371   0.0320
  -1.250   0.3124   0.01608   0.01061  -0.0749   0.6196   0.0343
  -1.000   0.3397   0.01547   0.00990  -0.0750   0.6018   0.0350
  -0.750   0.3673   0.01500   0.00932  -0.0751   0.5855   0.0360
  -0.500   0.3960   0.01518   0.00934  -0.0748   0.5701   0.0394
   0.000   0.4492   0.00981   0.00335  -0.0743   0.5457   0.0295
   0.250   0.4766   0.00951   0.00299  -0.0743   0.5329   0.0293
   0.500   0.5041   0.00931   0.00274  -0.0743   0.5200   0.0295
   0.750   0.5319   0.00917   0.00256  -0.0743   0.5075   0.0298
   1.000   0.5598   0.00909   0.00245  -0.0743   0.4948   0.0306
   1.250   0.5877   0.00907   0.00238  -0.0743   0.4805   0.0316
   1.500   0.6155   0.00908   0.00233  -0.0743   0.4656   0.0326
   1.750   0.6433   0.00912   0.00232  -0.0743   0.4505   0.0334
   2.000   0.6716   0.00920   0.00235  -0.0743   0.4363   0.0345
   2.250   0.6997   0.00932   0.00243  -0.0743   0.4231   0.0366
   2.500   0.7274   0.00940   0.00250  -0.0743   0.4107   0.0420
   2.750   0.7554   0.00974   0.00284  -0.0743   0.3972   0.0642
   3.000   0.7838   0.01009   0.00313  -0.0743   0.3865   0.0701
   3.250   0.8117   0.01034   0.00332  -0.0743   0.3758   0.0739
   3.500   0.8391   0.01046   0.00341  -0.0743   0.3643   0.0778
   3.750   0.8668   0.01070   0.00360  -0.0743   0.3534   0.0835
   4.000   0.8937   0.01067   0.00355  -0.0743   0.3431   0.0845
   4.250   0.9209   0.01057   0.00348  -0.0744   0.3353   0.0868
   4.500   0.9479   0.01075   0.00362  -0.0743   0.3268   0.0879
   4.750   0.9754   0.01098   0.00383  -0.0743   0.3194   0.0884
   5.250   1.0291   0.01086   0.00377  -0.0743   0.3037   0.0891
   5.500   1.0557   0.01088   0.00380  -0.0743   0.2948   0.0899
   5.750   1.0826   0.01093   0.00387  -0.0743   0.2856   0.0912
   6.000   1.1088   0.01127   0.00413  -0.0741   0.2745   0.0932
   6.250   1.1352   0.01123   0.00412  -0.0741   0.2614   0.0945
   6.500   1.1603   0.01157   0.00436  -0.0738   0.2395   0.0981
   6.750   1.1844   0.01186   0.00452  -0.0735   0.2086   0.1012
   7.000   1.2081   0.01227   0.00479  -0.0731   0.1828   0.1058
   7.250   1.2321   0.01262   0.00506  -0.0728   0.1659   0.1142
   7.500   1.2570   0.01286   0.00527  -0.0725   0.1545   0.1204
   7.750   1.2815   0.01317   0.00554  -0.0722   0.1448   0.1240
   8.000   1.3062   0.01345   0.00578  -0.0719   0.1369   0.1273
   8.500   0.9770   0.01382   0.00966  -0.1281   0.3199   0.0912
   8.750   1.3779   0.01444   0.00679  -0.0707   0.1099   0.1956
   9.000   1.4004   0.01489   0.00719  -0.0701   0.0976   0.2016
   9.250   1.4203   0.01554   0.00775  -0.0692   0.0784   0.2251
   9.500   1.4401   0.01617   0.00831  -0.0682   0.0658   0.2314
   9.750   1.4608   0.01668   0.00881  -0.0674   0.0589   0.2314
  10.000   1.4811   0.01721   0.00933  -0.0665   0.0518   0.2368
  10.250   1.4987   0.01791   0.00998  -0.0652   0.0402   0.2442
  10.500   1.5063   0.01933   0.01125  -0.0625   0.0183   0.2497
  10.750   1.5227   0.01999   0.01196  -0.0610   0.0162   0.2496
  11.250   1.5489   0.02127   0.01335  -0.0568   0.0147   0.2118
  11.500   1.5596   0.02210   0.01425  -0.0546   0.0141   0.2077
  11.750   1.5689   0.02311   0.01532  -0.0523   0.0134   0.2029
  12.000   1.5765   0.02426   0.01657  -0.0501   0.0129   0.1994
  12.250   1.5879   0.02519   0.01757  -0.0485   0.0127   0.1924
  12.500   1.5981   0.02624   0.01870  -0.0469   0.0124   0.1879
  12.750   1.6071   0.02743   0.01996  -0.0453   0.0121   0.1847
  13.000   1.6148   0.02878   0.02137  -0.0438   0.0117   0.1577
  13.250   1.6214   0.03027   0.02295  -0.0424   0.0114   0.1537
  13.500   1.6267   0.03196   0.02472  -0.0411   0.0111   0.1517
  13.750   1.6297   0.03393   0.02678  -0.0399   0.0108   0.1500
  14.000   1.6299   0.03628   0.02924  -0.0388   0.0106   0.1479
  14.250   1.6264   0.03912   0.03220  -0.0379   0.0104   0.1474
  14.500   1.6179   0.04270   0.03591  -0.0373   0.0101   0.1470
  14.750   1.6045   0.04708   0.04044  -0.0371   0.0100   0.1466
  15.000   1.6045   0.05003   0.04349  -0.0372   0.0099   0.1288
  15.750   1.5903   0.06135   0.05513  -0.0388   0.0096   0.1251
  16.000   1.5824   0.06580   0.05969  -0.0398   0.0095   0.1243
  16.500   1.5613   0.07569   0.06982  -0.0423   0.0094   0.1228
  16.750   1.5491   0.08102   0.07526  -0.0438   0.0093   0.1223
  17.000   1.5355   0.08661   0.08097  -0.0454   0.0092   0.1219
  17.250   1.5212   0.09244   0.08691  -0.0473   0.0092   0.1216
  17.500   1.5068   0.09841   0.09299  -0.0493   0.0091   0.1214
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