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GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 626 AIRFOIL (goe626-il)
Reynolds number: 100,000
Max Cl/Cd: 48.93 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe626-il-100000.txt
Download as CSV file: xf-goe626-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 626 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6088   0.06848   0.06314  -0.0663   1.0000   0.0906
 -10.500  -0.6668   0.06262   0.05729  -0.0661   1.0000   0.0897
 -10.250  -0.7296   0.05479   0.04932  -0.0704   1.0000   0.0883
 -10.000  -0.7571   0.04736   0.04146  -0.0773   1.0000   0.0882
  -9.750  -0.7593   0.04320   0.03691  -0.0798   1.0000   0.0891
  -9.500  -0.7528   0.03988   0.03313  -0.0816   1.0000   0.0906
  -9.250  -0.7390   0.03844   0.03180  -0.0804   1.0000   0.0925
  -9.000  -0.7243   0.03719   0.03059  -0.0796   1.0000   0.0947
  -8.750  -0.7090   0.03555   0.02882  -0.0796   1.0000   0.0972
  -8.500  -0.6922   0.03374   0.02674  -0.0799   1.0000   0.1001
  -8.250  -0.6761   0.03265   0.02575  -0.0790   1.0000   0.1031
  -8.000  -0.6593   0.03174   0.02492  -0.0783   1.0000   0.1073
  -7.750  -0.6246   0.03059   0.02380  -0.0811   0.9953   0.1155
  -7.500  -0.5812   0.02940   0.02271  -0.0858   0.9872   0.1331
  -7.250  -0.5349   0.02914   0.02276  -0.0904   0.9793   0.1652
  -7.000  -0.4900   0.03026   0.02395  -0.0933   0.9689   0.1905
  -6.750  -0.4484   0.03333   0.02735  -0.0932   0.9573   0.2006
  -6.250  -0.3576   0.03778   0.03188  -0.0957   0.9374   0.2222
  -6.000  -0.3222   0.04134   0.03566  -0.0928   0.9250   0.2253
  -5.750  -0.2767   0.04104   0.03517  -0.0966   0.9172   0.2382
  -5.500  -0.2399   0.04104   0.03504  -0.0986   0.9061   0.2506
  -5.250  -0.2048   0.04360   0.03777  -0.0960   0.8963   0.2551
  -5.000  -0.1637   0.04298   0.03699  -0.0993   0.8877   0.2703
  -4.750  -0.1163   0.04573   0.03993  -0.0969   0.8840   0.2753
  -4.250  -0.0416   0.04196   0.03575  -0.1049   0.8663   0.3033
  -4.000  -0.0223   0.04185   0.03570  -0.1025   0.8529   0.3089
  -3.750   0.0308   0.03940   0.03294  -0.1095   0.8490   0.3247
  -3.500   0.0508   0.03990   0.03359  -0.1058   0.8372   0.3290
  -3.250   0.1019   0.03790   0.03135  -0.1117   0.8322   0.3444
  -3.000   0.1477   0.03786   0.03142  -0.1120   0.8290   0.3551
  -2.750   0.1708   0.03649   0.02989  -0.1131   0.8153   0.3648
  -2.500   0.2173   0.03547   0.02884  -0.1153   0.8109   0.3734
  -2.250   0.2468   0.03379   0.02689  -0.1181   0.7977   0.3789
  -2.000   0.2932   0.03215   0.02513  -0.1215   0.7921   0.3844
  -1.750   0.3157   0.03161   0.02459  -0.1204   0.7790   0.3888
  -1.500   0.3637   0.03006   0.02282  -0.1245   0.7725   0.3934
  -1.250   0.3904   0.02916   0.02174  -0.1253   0.7589   0.3968
  -1.000   0.4286   0.02803   0.02034  -0.1279   0.7490   0.4010
  -0.750   0.4595   0.02725   0.01953  -0.1282   0.7378   0.4037
  -0.500   0.4871   0.02675   0.01896  -0.1281   0.7256   0.4067
  -0.250   0.5264   0.02600   0.01803  -0.1300   0.7166   0.4112
   0.000   0.5514   0.02564   0.01755  -0.1298   0.7033   0.4145
   0.250   0.5844   0.02515   0.01685  -0.1309   0.6923   0.4171
   0.500   0.6177   0.02468   0.01618  -0.1320   0.6815   0.4203
   0.750   0.6421   0.02452   0.01603  -0.1312   0.6697   0.4235
   1.000   0.6773   0.02424   0.01560  -0.1323   0.6607   0.4272
   1.250   0.6998   0.02428   0.01561  -0.1315   0.6487   0.4299
   1.500   0.7338   0.02413   0.01527  -0.1325   0.6398   0.4331
   1.750   0.7574   0.02425   0.01532  -0.1319   0.6285   0.4367
   2.000   0.7894   0.02424   0.01516  -0.1326   0.6201   0.4405
   2.250   0.8108   0.02443   0.01542  -0.1315   0.6101   0.4439
   2.500   0.8446   0.02448   0.01533  -0.1324   0.6028   0.4478
   2.750   0.8633   0.02479   0.01572  -0.1310   0.5925   0.4510
   3.000   0.8957   0.02483   0.01558  -0.1316   0.5843   0.4553
   3.250   0.9157   0.02513   0.01594  -0.1303   0.5744   0.4592
   3.500   0.9440   0.02518   0.01597  -0.1301   0.5663   0.4642
   3.750   0.9673   0.02549   0.01632  -0.1294   0.5581   0.4695
   4.000   0.9919   0.02569   0.01651  -0.1287   0.5496   0.4749
   4.250   1.0225   0.02578   0.01652  -0.1290   0.5427   0.4802
   4.500   1.0396   0.02614   0.01705  -0.1272   0.5338   0.4853
   4.750   1.0698   0.02622   0.01706  -0.1274   0.5271   0.4927
   5.000   1.0898   0.02657   0.01752  -0.1260   0.5192   0.4996
   5.250   1.1142   0.02666   0.01766  -0.1252   0.5109   0.5088
   5.500   1.1432   0.02677   0.01773  -0.1252   0.5038   0.5196
   5.750   1.1611   0.02715   0.01827  -0.1235   0.4955   0.5305
   6.000   1.1921   0.02717   0.01829  -0.1238   0.4894   0.5453
   6.250   1.2113   0.02762   0.01892  -0.1224   0.4823   0.5620
   6.500   1.2333   0.02785   0.01933  -0.1213   0.4750   0.5879
   6.750   1.2673   0.02748   0.01921  -0.1219   0.4691   0.6650
   7.000   1.2766   0.02769   0.01996  -0.1188   0.4605   1.0000
   7.250   1.3079   0.02775   0.01979  -0.1190   0.4526   1.0000
   7.500   1.3239   0.02830   0.02038  -0.1170   0.4437   1.0000
   7.750   1.3513   0.02832   0.02026  -0.1165   0.4346   1.0000
   8.000   1.3666   0.02880   0.02077  -0.1144   0.4250   1.0000
   8.250   1.3950   0.02875   0.02055  -0.1140   0.4154   1.0000
   8.500   1.4051   0.02934   0.02126  -0.1111   0.4055   1.0000
   8.750   1.4355   0.02934   0.02107  -0.1111   0.3962   1.0000
   9.000   1.4401   0.03003   0.02194  -0.1075   0.3861   1.0000
   9.250   1.4696   0.03011   0.02183  -0.1074   0.3766   1.0000
   9.500   1.4711   0.03081   0.02271  -0.1033   0.3662   1.0000
   9.750   1.4908   0.03111   0.02293  -0.1018   0.3565   1.0000
  10.000   1.4974   0.03167   0.02355  -0.0985   0.3462   1.0000
  10.250   1.5068   0.03222   0.02412  -0.0956   0.3369   1.0000
  10.500   1.5159   0.03270   0.02456  -0.0927   0.3271   1.0000
  10.750   1.5179   0.03352   0.02545  -0.0890   0.3179   1.0000
  11.000   1.5297   0.03402   0.02589  -0.0867   0.3089   1.0000
  11.250   1.5290   0.03512   0.02709  -0.0831   0.3003   1.0000
  11.500   1.5389   0.03574   0.02766  -0.0808   0.2918   1.0000
  11.750   1.5360   0.03705   0.02908  -0.0774   0.2835   1.0000
  12.000   1.5434   0.03793   0.02994  -0.0751   0.2756   1.0000
  12.250   1.5439   0.03936   0.03145  -0.0725   0.2683   1.0000
  12.500   1.5462   0.04067   0.03281  -0.0702   0.2608   1.0000
  12.750   1.5502   0.04203   0.03419  -0.0681   0.2537   1.0000
  13.000   1.5467   0.04389   0.03617  -0.0658   0.2463   1.0000
  13.250   1.5535   0.04518   0.03739  -0.0642   0.2391   1.0000
  13.500   1.5447   0.04766   0.04005  -0.0621   0.2319   1.0000
  13.750   1.5519   0.04902   0.04129  -0.0608   0.2240   1.0000
  14.000   1.5387   0.05215   0.04463  -0.0591   0.2165   1.0000
  14.250   1.5423   0.05395   0.04633  -0.0580   0.2079   1.0000
  14.500   1.5299   0.05737   0.04988  -0.0569   0.1995   1.0000
  14.750   1.5276   0.06005   0.05251  -0.0561   0.1902   1.0000
  15.000   1.5388   0.06152   0.05372  -0.0551   0.1793   1.0000
  15.250   1.5195   0.06627   0.05871  -0.0548   0.1717   1.0000
  15.500   1.5347   0.06765   0.05987  -0.0540   0.1630   1.0000
  15.750   1.5222   0.07198   0.06441  -0.0540   0.1572   1.0000
  16.000   1.5528   0.07188   0.06403  -0.0530   0.1506   1.0000
  16.250   1.5382   0.07659   0.06900  -0.0532   0.1473   1.0000
  16.500   1.5271   0.08106   0.07369  -0.0537   0.1440   1.0000
  16.750   1.5290   0.08408   0.07679  -0.0538   0.1408   1.0000
  17.000   1.5597   0.08391   0.07647  -0.0528   0.1375   1.0000
  17.250   1.5596   0.08746   0.08015  -0.0530   0.1355   1.0000
  17.500   1.5319   0.09420   0.08722  -0.0548   0.1343   1.0000
  17.750   1.4970   0.10240   0.09576  -0.0577   0.1333   1.0000
  18.000   1.4313   0.11604   0.10982  -0.0641   0.1328   1.0000
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