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GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 701 AIRFOIL (goe701-il)
Reynolds number: 100,000
Max Cl/Cd: 54.75 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe701-il-100000.txt
Download as CSV file: xf-goe701-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 701 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3815   0.10571   0.10124  -0.0199   1.0000   0.1363
  -7.750  -0.4049   0.10493   0.10054  -0.0184   1.0000   0.1390
  -7.500  -0.4462   0.10378   0.09945  -0.0294   0.9911   0.1414
  -7.250  -0.4204   0.09838   0.09405  -0.0271   0.9883   0.1433
  -7.000  -0.3878   0.09491   0.09054  -0.0267   0.9849   0.1469
  -6.750  -0.3768   0.09187   0.08747  -0.0307   0.9774   0.1530
  -6.500  -0.3784   0.08656   0.08209  -0.0425   0.9661   0.1589
  -6.250  -0.3566   0.08393   0.07948  -0.0401   0.9612   0.1618
  -6.000  -0.3544   0.08034   0.07555  -0.0542   0.9476   0.1739
  -5.750  -0.3321   0.07602   0.07136  -0.0517   0.9437   0.1755
  -5.500  -0.3032   0.07346   0.06883  -0.0512   0.9402   0.1800
  -5.250  -0.2991   0.06993   0.06504  -0.0577   0.9287   0.1917
  -5.000  -0.2714   0.06686   0.06203  -0.0575   0.9249   0.1947
  -4.750  -0.2608   0.06486   0.06000  -0.0567   0.9163   0.1998
  -4.500  -0.2363   0.06133   0.05630  -0.0612   0.9100   0.2113
  -4.250  -0.2194   0.04594   0.03927  -0.0712   0.9024   0.1424
  -4.000  -0.1936   0.04459   0.03802  -0.0717   0.8961   0.1451
  -3.750  -0.1570   0.04181   0.03488  -0.0744   0.8922   0.1467
  -3.500  -0.1452   0.03980   0.03254  -0.0726   0.8831   0.1466
  -3.250  -0.1116   0.03771   0.03008  -0.0741   0.8782   0.1488
  -3.000  -0.0866   0.03639   0.02841  -0.0740   0.8716   0.1535
  -2.750  -0.0608   0.03502   0.02648  -0.0737   0.8645   0.1578
  -2.500  -0.0215   0.03385   0.02536  -0.0760   0.8606   0.1634
  -2.250  -0.0060   0.03357   0.02491  -0.0741   0.8513   0.1698
  -2.000   0.0298   0.03258   0.02368  -0.0754   0.8461   0.1778
  -1.750   0.0598   0.03214   0.02314  -0.0758   0.8401   0.1862
  -1.500   0.0830   0.03174   0.02262  -0.0751   0.8318   0.1947
  -1.250   0.1258   0.03113   0.02181  -0.0773   0.8279   0.2070
  -1.000   0.1388   0.03110   0.02187  -0.0751   0.8179   0.2141
  -0.750   0.1780   0.03052   0.02118  -0.0768   0.8130   0.2265
  -0.500   0.2032   0.03040   0.02109  -0.0764   0.8056   0.2370
  -0.250   0.2320   0.03007   0.02080  -0.0765   0.7982   0.2480
   0.000   0.2776   0.02928   0.02001  -0.0790   0.7947   0.2622
   0.250   0.2889   0.02965   0.02042  -0.0764   0.7837   0.2714
   0.500   0.3320   0.02888   0.01974  -0.0785   0.7795   0.2898
   0.750   0.3661   0.02846   0.01942  -0.0792   0.7735   0.3102
   1.000   0.3917   0.02826   0.01942  -0.0787   0.7647   0.3369
   1.250   0.4457   0.02671   0.01842  -0.0824   0.7622   0.4368
   1.500   0.6045   0.02322   0.01595  -0.1045   0.7624   1.0000
   1.750   0.6297   0.02300   0.01561  -0.1032   0.7509   1.0000
   2.000   0.6840   0.02192   0.01440  -0.1065   0.7452   1.0000
   2.250   0.6998   0.02218   0.01460  -0.1040   0.7340   1.0000
   2.500   0.7465   0.02147   0.01380  -0.1063   0.7281   1.0000
   2.750   0.7613   0.02175   0.01405  -0.1037   0.7165   1.0000
   3.000   0.8095   0.02100   0.01321  -0.1063   0.7103   1.0000
   3.250   0.8222   0.02131   0.01351  -0.1032   0.6979   1.0000
   3.500   0.8510   0.02116   0.01332  -0.1027   0.6881   1.0000
   3.750   0.8854   0.02080   0.01290  -0.1031   0.6784   1.0000
   4.000   0.9042   0.02088   0.01298  -0.1010   0.6657   1.0000
   4.250   0.9314   0.02072   0.01279  -0.1002   0.6540   1.0000
   4.500   0.9696   0.02028   0.01226  -0.1012   0.6433   1.0000
   4.750   0.9878   0.02034   0.01232  -0.0989   0.6289   1.0000
   5.000   1.0089   0.02032   0.01228  -0.0971   0.6140   1.0000
   5.250   1.0315   0.02026   0.01219  -0.0955   0.5983   1.0000
   5.500   1.0543   0.02021   0.01209  -0.0940   0.5816   1.0000
   5.750   1.0771   0.02020   0.01201  -0.0924   0.5637   1.0000
   6.000   1.1004   0.02022   0.01192  -0.0910   0.5445   1.0000
   6.250   1.1137   0.02048   0.01215  -0.0880   0.5227   1.0000
   6.500   1.1310   0.02072   0.01228  -0.0856   0.5004   1.0000
   6.750   1.1513   0.02103   0.01240  -0.0839   0.4788   1.0000
   7.000   1.1638   0.02153   0.01285  -0.0810   0.4570   1.0000
   7.250   1.1795   0.02206   0.01326  -0.0786   0.4368   1.0000
   7.500   1.1964   0.02263   0.01372  -0.0766   0.4189   1.0000
   7.750   1.2136   0.02325   0.01425  -0.0747   0.4030   1.0000
   8.000   1.2308   0.02391   0.01485  -0.0729   0.3884   1.0000
   8.250   1.2491   0.02459   0.01546  -0.0713   0.3754   1.0000
   8.500   1.2707   0.02528   0.01604  -0.0703   0.3635   1.0000
   8.750   1.2866   0.02598   0.01676  -0.0684   0.3522   1.0000
   9.000   1.3043   0.02677   0.01759  -0.0669   0.3422   1.0000
   9.250   1.3312   0.02755   0.01823  -0.0669   0.3325   1.0000
   9.500   1.3412   0.02834   0.01919  -0.0641   0.3235   1.0000
   9.750   1.3634   0.02915   0.01994  -0.0634   0.3143   1.0000
  10.000   1.3746   0.02989   0.02076  -0.0609   0.3052   1.0000
  10.250   1.3886   0.03068   0.02156  -0.0589   0.2962   1.0000
  10.500   1.4029   0.03138   0.02226  -0.0569   0.2873   1.0000
  10.750   1.4123   0.03226   0.02324  -0.0542   0.2796   1.0000
  11.000   1.4268   0.03300   0.02398  -0.0524   0.2715   1.0000
  11.250   1.4367   0.03393   0.02501  -0.0499   0.2644   1.0000
  11.500   1.4445   0.03470   0.02585  -0.0472   0.2569   1.0000
  11.750   1.4574   0.03561   0.02678  -0.0453   0.2497   1.0000
  12.000   1.4592   0.03656   0.02791  -0.0419   0.2433   1.0000
  12.250   1.4793   0.03731   0.02858  -0.0412   0.2359   1.0000
  12.500   1.4714   0.03847   0.03001  -0.0368   0.2302   1.0000
  12.750   1.4824   0.03917   0.03069  -0.0349   0.2232   1.0000
  13.000   1.4825   0.04040   0.03208  -0.0320   0.2175   1.0000
  13.250   1.4802   0.04162   0.03348  -0.0290   0.2117   1.0000
  13.500   1.4921   0.04234   0.03414  -0.0275   0.2049   1.0000
  13.750   1.4782   0.04415   0.03626  -0.0238   0.1996   1.0000
  14.000   1.4765   0.04531   0.03747  -0.0215   0.1928   1.0000
  14.250   1.4682   0.04714   0.03947  -0.0190   0.1867   1.0000
  14.500   1.4583   0.04913   0.04163  -0.0167   0.1799   1.0000
  14.750   1.4506   0.05115   0.04374  -0.0150   0.1731   1.0000
  15.000   1.4370   0.05394   0.04675  -0.0134   0.1657   1.0000
  15.250   1.4245   0.05688   0.04981  -0.0123   0.1577   1.0000
  15.500   1.4104   0.06030   0.05335  -0.0117   0.1489   1.0000
  15.750   1.3938   0.06454   0.05778  -0.0116   0.1388   1.0000
  16.000   1.3754   0.06932   0.06264  -0.0121   0.1275   1.0000
  16.250   1.3562   0.07461   0.06794  -0.0129   0.1166   1.0000
  16.500   1.3369   0.08022   0.07352  -0.0141   0.1070   1.0000
  16.750   1.3174   0.08616   0.07946  -0.0156   0.0984   1.0000
  17.000   1.3000   0.09204   0.08539  -0.0172   0.0910   1.0000
  17.250   1.2857   0.09745   0.09069  -0.0187   0.0853   1.0000
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