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GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 387 AIRFOIL (goe387-il)
Reynolds number: 500,000
Max Cl/Cd: 100.97 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe387-il-500000.txt
Download as CSV file: xf-goe387-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 387 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1453   0.10799   0.10560  -0.0648   0.9701   0.0313
 -10.750  -0.1296   0.10391   0.10151  -0.0692   0.9597   0.0320
 -10.500  -0.1329   0.09421   0.09177  -0.0819   0.9489   0.0336
 -10.250  -0.1022   0.09085   0.08839  -0.0861   0.9413   0.0339
 -10.000  -0.0680   0.08740   0.08488  -0.0923   0.9320   0.0342
  -9.750  -0.0319   0.08366   0.08108  -0.0998   0.9204   0.0348
  -9.500   0.0002   0.07941   0.07672  -0.1079   0.9038   0.0358
  -9.250  -0.0186   0.06744   0.06457  -0.1230   0.8721   0.0384
  -9.000  -0.0040   0.06617   0.06322  -0.1223   0.8539   0.0387
  -8.750   0.0060   0.06478   0.06174  -0.1218   0.8368   0.0390
  -8.500   0.0097   0.06265   0.05955  -0.1220   0.8213   0.0392
  -8.250   0.0120   0.06056   0.05742  -0.1220   0.8078   0.0395
  -8.000   0.0073   0.05786   0.05467  -0.1225   0.7946   0.0399
  -7.750  -0.0074   0.05468   0.05144  -0.1230   0.7819   0.0401
  -7.500  -0.0168   0.05075   0.04745  -0.1244   0.7714   0.0406
  -7.250  -0.0864   0.03729   0.03314  -0.1260   0.7610   0.0442
  -7.000  -0.0690   0.03574   0.03164  -0.1253   0.7532   0.0445
  -6.750  -0.0526   0.03450   0.03034  -0.1244   0.7456   0.0449
  -6.500  -0.0365   0.03327   0.02904  -0.1234   0.7387   0.0455
  -6.250  -0.0218   0.03180   0.02747  -0.1223   0.7315   0.0464
  -6.000  -0.0210   0.02861   0.02365  -0.1195   0.7250   0.0507
  -5.750  -0.0002   0.02745   0.02252  -0.1189   0.7185   0.0514
  -5.500   0.0203   0.02649   0.02152  -0.1180   0.7119   0.0524
  -5.250   0.0326   0.02500   0.01949  -0.1157   0.7057   0.0576
  -5.000   0.0548   0.02379   0.01837  -0.1151   0.6988   0.0586
  -4.750   0.0767   0.02297   0.01747  -0.1142   0.6919   0.0601
  -4.500   0.0953   0.02198   0.01618  -0.1128   0.6860   0.0659
  -4.250   0.1140   0.01762   0.01091  -0.1092   0.6809   0.0428
  -4.000   0.1378   0.01618   0.00928  -0.1082   0.6756   0.0404
  -3.750   0.1630   0.01555   0.00832  -0.1071   0.6706   0.0389
  -3.500   0.1883   0.01485   0.00760  -0.1065   0.6654   0.0392
  -3.250   0.2139   0.01430   0.00701  -0.1059   0.6600   0.0392
  -3.000   0.2397   0.01382   0.00644  -0.1052   0.6550   0.0392
  -2.750   0.2656   0.01339   0.00597  -0.1047   0.6503   0.0392
  -2.500   0.2909   0.01296   0.00555  -0.1040   0.6451   0.0393
  -2.250   0.3159   0.01257   0.00515  -0.1033   0.6398   0.0397
  -2.000   0.3412   0.01230   0.00483  -0.1026   0.6347   0.0401
  -1.750   0.3661   0.01201   0.00456  -0.1018   0.6295   0.0406
  -1.500   0.3910   0.01176   0.00431  -0.1011   0.6241   0.0412
  -1.250   0.4161   0.01156   0.00408  -0.1003   0.6190   0.0417
  -1.000   0.4415   0.01141   0.00390  -0.0997   0.6141   0.0426
  -0.750   0.4667   0.01126   0.00376  -0.0990   0.6085   0.0436
  -0.500   0.4911   0.01103   0.00352  -0.0981   0.6028   0.0450
  -0.250   0.5163   0.01091   0.00337  -0.0974   0.5972   0.0463
   0.000   0.5413   0.01079   0.00326  -0.0967   0.5910   0.0481
   0.250   0.5665   0.01072   0.00314  -0.0959   0.5846   0.0504
   0.500   0.5915   0.01064   0.00306  -0.0952   0.5787   0.0555
   0.750   0.6134   0.01023   0.00302  -0.0940   0.5721   0.1624
   1.000   0.6331   0.00975   0.00307  -0.0926   0.5657   0.3507
   1.250   0.6476   0.00909   0.00316  -0.0900   0.5594   0.5965
   1.500   0.7882   0.00860   0.00348  -0.1140   0.5445   0.9953
   1.750   0.8298   0.00868   0.00347  -0.1169   0.5335   1.0000
   2.000   0.8515   0.00878   0.00350  -0.1156   0.5241   1.0000
   2.250   0.8727   0.00890   0.00354  -0.1142   0.5143   1.0000
   2.500   0.8945   0.00901   0.00360  -0.1129   0.5043   1.0000
   2.750   0.9149   0.00917   0.00367  -0.1114   0.4943   1.0000
   3.000   0.9362   0.00931   0.00376  -0.1100   0.4836   1.0000
   3.250   0.9567   0.00948   0.00386  -0.1085   0.4732   1.0000
   3.750   0.9966   0.00987   0.00411  -0.1053   0.4515   1.0000
   4.000   1.0160   0.01009   0.00425  -0.1036   0.4420   1.0000
   4.250   1.0357   0.01029   0.00441  -0.1020   0.4326   1.0000
   4.500   1.0552   0.01052   0.00458  -0.1003   0.4243   1.0000
   4.750   1.0745   0.01073   0.00475  -0.0987   0.4161   1.0000
   5.000   1.0933   0.01097   0.00494  -0.0969   0.4090   1.0000
   5.250   1.1132   0.01117   0.00512  -0.0954   0.4022   1.0000
   5.500   1.1307   0.01145   0.00534  -0.0934   0.3957   1.0000
   5.750   1.1504   0.01165   0.00554  -0.0919   0.3898   1.0000
   6.000   1.1692   0.01188   0.00575  -0.0902   0.3842   1.0000
   6.250   1.1851   0.01217   0.00599  -0.0879   0.3790   1.0000
   6.500   1.2023   0.01237   0.00620  -0.0859   0.3743   1.0000
   6.750   1.2189   0.01258   0.00642  -0.0838   0.3691   1.0000
   7.000   1.2342   0.01286   0.00667  -0.0815   0.3643   1.0000
   7.250   1.2504   0.01316   0.00694  -0.0795   0.3600   1.0000
   7.500   1.2692   0.01336   0.00719  -0.0779   0.3560   1.0000
   7.750   1.2867   0.01363   0.00747  -0.0761   0.3516   1.0000
   8.000   1.3031   0.01396   0.00778  -0.0743   0.3475   1.0000
   8.250   1.3197   0.01431   0.00812  -0.0725   0.3433   1.0000
   8.500   1.3378   0.01456   0.00843  -0.0710   0.3379   1.0000
   8.750   1.3538   0.01493   0.00879  -0.0692   0.3326   1.0000
   9.000   1.3682   0.01538   0.00922  -0.0672   0.3270   1.0000
   9.250   1.3865   0.01568   0.00958  -0.0659   0.3218   1.0000
   9.500   1.4021   0.01612   0.01002  -0.0643   0.3166   1.0000
   9.750   1.4155   0.01668   0.01056  -0.0624   0.3114   1.0000
  10.000   1.4336   0.01704   0.01100  -0.0612   0.3063   1.0000
  10.250   1.4488   0.01756   0.01153  -0.0597   0.3007   1.0000
  10.500   1.4611   0.01824   0.01220  -0.0579   0.2953   1.0000
  10.750   1.4783   0.01870   0.01274  -0.0568   0.2896   1.0000
  11.000   1.4910   0.01941   0.01346  -0.0552   0.2827   1.0000
  11.250   1.5044   0.02013   0.01420  -0.0538   0.2756   1.0000
  11.500   1.5160   0.02097   0.01506  -0.0523   0.2673   1.0000
  11.750   1.5276   0.02185   0.01596  -0.0508   0.2586   1.0000
  12.000   1.5348   0.02304   0.01712  -0.0491   0.2477   1.0000
  12.250   1.5414   0.02434   0.01839  -0.0475   0.2351   1.0000
  12.500   1.5480   0.02568   0.01973  -0.0459   0.2232   1.0000
  12.750   1.5527   0.02721   0.02123  -0.0444   0.2127   1.0000
  13.000   1.5550   0.02897   0.02296  -0.0427   0.2033   1.0000
  13.250   1.5592   0.03064   0.02463  -0.0414   0.1959   1.0000
  13.500   1.5622   0.03245   0.02644  -0.0400   0.1903   1.0000
  13.750   1.5663   0.03423   0.02825  -0.0388   0.1842   1.0000
  14.000   1.5681   0.03623   0.03026  -0.0377   0.1798   1.0000
  14.250   1.5731   0.03801   0.03209  -0.0367   0.1755   1.0000
  14.500   1.5790   0.03976   0.03389  -0.0359   0.1719   1.0000
  14.750   1.5804   0.04194   0.03610  -0.0350   0.1677   1.0000
  15.000   1.5800   0.04433   0.03850  -0.0340   0.1640   1.0000
  15.250   1.5883   0.04595   0.04022  -0.0335   0.1605   1.0000
  15.500   1.5916   0.04809   0.04242  -0.0329   0.1564   1.0000
  15.750   1.5906   0.05069   0.04504  -0.0323   0.1524   1.0000
  16.000   1.5933   0.05296   0.04737  -0.0319   0.1481   1.0000
  16.250   1.5970   0.05519   0.04968  -0.0315   0.1437   1.0000
  16.500   1.5960   0.05793   0.05245  -0.0312   0.1395   1.0000
  16.750   1.5963   0.06059   0.05517  -0.0309   0.1343   1.0000
  17.000   1.5964   0.06334   0.05798  -0.0308   0.1284   1.0000
  17.250   1.5918   0.06663   0.06131  -0.0307   0.1225   1.0000
  17.500   1.5877   0.06995   0.06466  -0.0308   0.1149   1.0000
  17.750   1.5804   0.07371   0.06844  -0.0309   0.1075   1.0000
  18.000   1.5689   0.07806   0.07280  -0.0312   0.1010   1.0000
  18.250   1.5582   0.08234   0.07712  -0.0316   0.0953   1.0000
  18.500   1.5456   0.08696   0.08176  -0.0322   0.0912   1.0000
  18.750   1.5366   0.09116   0.08601  -0.0328   0.0878   1.0000
  19.000   1.5257   0.09565   0.09055  -0.0336   0.0849   1.0000
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