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GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 500 AIRFOIL (goe500-il)
Reynolds number: 100,000
Max Cl/Cd: 64.36 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe500-il-100000.txt
Download as CSV file: xf-goe500-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 500 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3796   0.10792   0.10367  -0.0185   1.0000   0.1043
  -7.000  -0.4022   0.10792   0.10376  -0.0164   1.0000   0.1055
  -6.750  -0.4129   0.10736   0.10326  -0.0290   0.9950   0.1071
  -6.500  -0.3972   0.10145   0.09736  -0.0261   0.9919   0.1085
  -6.250  -0.3755   0.09759   0.09345  -0.0242   0.9880   0.1112
  -6.000  -0.3524   0.09414   0.08997  -0.0287   0.9827   0.1167
  -5.750  -0.3303   0.08893   0.08472  -0.0470   0.9719   0.1235
  -5.500  -0.3161   0.08609   0.08189  -0.0420   0.9679   0.1261
  -5.250  -0.2705   0.08041   0.07602  -0.0661   0.9577   0.1383
  -5.000  -0.2630   0.07728   0.07295  -0.0602   0.9527   0.1397
  -4.750  -0.2512   0.07524   0.07092  -0.0565   0.9464   0.1432
  -4.500  -0.2079   0.07029   0.06583  -0.0688   0.9410   0.1562
  -4.250  -0.1818   0.06747   0.06291  -0.0745   0.9322   0.1678
  -4.000  -0.0810   0.04835   0.04257  -0.1092   0.9301   0.1224
  -3.750  -0.0199   0.03900   0.03219  -0.1208   0.9284   0.1068
  -3.500   0.0289   0.03572   0.02856  -0.1265   0.9253   0.1103
  -3.250   0.0556   0.03443   0.02708  -0.1272   0.9162   0.1145
  -3.000   0.1050   0.03210   0.02407  -0.1318   0.9116   0.1194
  -2.750   0.1390   0.03084   0.02253  -0.1334   0.9044   0.1273
  -2.500   0.1779   0.02982   0.02113  -0.1354   0.8979   0.1390
  -2.250   0.2239   0.02880   0.02010  -0.1388   0.8941   0.1571
  -2.000   0.2450   0.02850   0.01978  -0.1379   0.8844   0.1732
  -1.750   0.2880   0.02807   0.01925  -0.1405   0.8797   0.1995
  -1.500   0.3113   0.02800   0.01924  -0.1399   0.8706   0.2178
  -1.250   0.3507   0.02769   0.01901  -0.1419   0.8653   0.2412
  -1.000   0.3776   0.02765   0.01894  -0.1418   0.8570   0.2612
  -0.750   0.4146   0.02728   0.01866  -0.1433   0.8510   0.2859
  -0.500   0.4488   0.02696   0.01845  -0.1443   0.8447   0.3198
  -0.250   0.4790   0.02664   0.01832  -0.1445   0.8368   0.3755
   0.000   0.5237   0.02600   0.01798  -0.1470   0.8333   0.4582
   0.250   0.5433   0.02615   0.01827  -0.1455   0.8226   0.5114
   0.500   0.5877   0.02550   0.01782  -0.1477   0.8190   0.5867
   0.750   0.6093   0.02542   0.01796  -0.1465   0.8087   0.6609
   1.000   0.6530   0.02416   0.01718  -0.1482   0.8049   1.0000
   1.250   0.6792   0.02441   0.01726  -0.1480   0.7952   1.0000
   1.500   0.7225   0.02401   0.01672  -0.1501   0.7906   1.0000
   1.750   0.7647   0.02356   0.01616  -0.1519   0.7864   1.0000
   2.000   0.7902   0.02369   0.01623  -0.1513   0.7761   1.0000
   2.250   0.8355   0.02301   0.01549  -0.1534   0.7730   1.0000
   2.500   0.8564   0.02336   0.01582  -0.1521   0.7614   1.0000
   2.750   0.9010   0.02267   0.01509  -0.1540   0.7580   1.0000
   3.000   0.9227   0.02299   0.01541  -0.1528   0.7463   1.0000
   3.250   0.9674   0.02227   0.01468  -0.1548   0.7425   1.0000
   3.500   0.9881   0.02269   0.01511  -0.1535   0.7306   1.0000
   3.750   1.0169   0.02276   0.01522  -0.1533   0.7216   1.0000
   4.000   1.0526   0.02249   0.01495  -0.1540   0.7143   1.0000
   4.250   1.0766   0.02284   0.01535  -0.1532   0.7038   1.0000
   4.500   1.1157   0.02246   0.01500  -0.1543   0.6975   1.0000
   4.750   1.1369   0.02292   0.01552  -0.1531   0.6858   1.0000
   5.000   1.1664   0.02288   0.01552  -0.1528   0.6755   1.0000
   5.250   1.2035   0.02246   0.01511  -0.1535   0.6663   1.0000
   5.500   1.2244   0.02288   0.01563  -0.1521   0.6542   1.0000
   5.750   1.2496   0.02320   0.01604  -0.1514   0.6440   1.0000
   6.000   1.2827   0.02293   0.01578  -0.1514   0.6329   1.0000
   6.250   1.3098   0.02268   0.01558  -0.1504   0.6176   1.0000
   6.500   1.3317   0.02245   0.01540  -0.1484   0.5984   1.0000
   6.750   1.3553   0.02210   0.01504  -0.1466   0.5778   1.0000
   7.000   1.3780   0.02182   0.01474  -0.1447   0.5558   1.0000
   7.250   1.3943   0.02190   0.01488  -0.1421   0.5336   1.0000
   7.500   1.4140   0.02197   0.01496  -0.1401   0.5124   1.0000
   7.750   1.4264   0.02226   0.01533  -0.1370   0.4877   1.0000
   8.000   1.4372   0.02259   0.01566  -0.1335   0.4586   1.0000
   8.250   1.4419   0.02312   0.01614  -0.1291   0.4218   1.0000
   8.500   1.4346   0.02398   0.01687  -0.1230   0.3707   1.0000
   8.750   1.4142   0.02570   0.01806  -0.1155   0.2775   1.0000
   9.000   1.3885   0.02873   0.02030  -0.1087   0.1914   1.0000
   9.250   1.3694   0.03198   0.02300  -0.1035   0.1394   1.0000
   9.500   1.3602   0.03472   0.02555  -0.0996   0.1184   1.0000
   9.750   1.3553   0.03724   0.02800  -0.0965   0.1070   1.0000
  10.000   1.3513   0.03982   0.03049  -0.0936   0.0989   1.0000
  10.250   1.3560   0.04186   0.03260  -0.0914   0.0916   1.0000
  10.500   1.3603   0.04417   0.03475  -0.0893   0.0858   1.0000
  10.750   1.3721   0.04588   0.03662  -0.0876   0.0801   1.0000
  11.000   1.3893   0.04763   0.03823  -0.0863   0.0749   1.0000
  11.250   1.4162   0.04923   0.03990  -0.0854   0.0702   1.0000
  11.500   1.4375   0.05097   0.04170  -0.0845   0.0658   1.0000
  11.750   1.4965   0.05355   0.04422  -0.0865   0.0612   1.0000
  12.000   1.5107   0.05591   0.04692  -0.0850   0.0591   1.0000
  12.250   1.5245   0.05850   0.04978  -0.0837   0.0568   1.0000
  12.500   1.5416   0.06157   0.05310  -0.0828   0.0553   1.0000
  12.750   1.5548   0.06500   0.05681  -0.0816   0.0545   1.0000
  13.000   1.5617   0.06858   0.06067  -0.0802   0.0536   1.0000
  13.250   1.5662   0.07261   0.06492  -0.0789   0.0526   1.0000
  13.500   1.5684   0.07812   0.07069  -0.0780   0.0518   1.0000
  13.750   1.5573   0.08329   0.07617  -0.0762   0.0515   1.0000
  14.000   1.5410   0.08783   0.08098  -0.0744   0.0515   1.0000
  14.250   1.5231   0.09189   0.08536  -0.0729   0.0516   1.0000
  14.500   1.5029   0.09589   0.08965  -0.0718   0.0518   1.0000
  14.750   1.4785   0.10028   0.09434  -0.0715   0.0522   1.0000
  15.000   1.4457   0.10585   0.10028  -0.0724   0.0529   1.0000
  15.250   1.3679   0.11796   0.11300  -0.0785   0.0559   1.0000
  15.500   1.3287   0.12846   0.12378  -0.0844   0.0576   1.0000
  15.750   1.2967   0.13909   0.13458  -0.0909   0.0592   1.0000
  16.000   1.2729   0.14927   0.14486  -0.0972   0.0606   1.0000
  16.250   1.2596   0.15807   0.15370  -0.1020   0.0616   1.0000
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