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GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 573 AIRFOIL (goe573-il)
Reynolds number: 100,000
Max Cl/Cd: 47.11 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe573-il-100000-n5.txt
Download as CSV file: xf-goe573-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 573 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2128   0.14021   0.13553  -0.0431   1.0000   0.0396
 -11.750  -0.2167   0.13850   0.13390  -0.0443   1.0000   0.0398
 -11.500  -0.2236   0.13714   0.13262  -0.0457   1.0000   0.0400
 -11.250  -0.2259   0.13490   0.13047  -0.0462   1.0000   0.0401
 -11.000  -0.1965   0.12757   0.12314  -0.0444   0.9985   0.0415
 -10.750  -0.1751   0.12285   0.11840  -0.0485   0.9906   0.0426
 -10.500  -0.1609   0.11893   0.11450  -0.0514   0.9746   0.0438
 -10.250  -0.1520   0.11553   0.11113  -0.0532   0.9439   0.0449
 -10.000  -0.1356   0.11142   0.10699  -0.0581   0.9235   0.0470
  -9.750  -0.1212   0.10770   0.10322  -0.0666   0.9072   0.0493
  -9.500  -0.1048   0.10377   0.09922  -0.0775   0.8909   0.0499
  -9.250  -0.0674   0.09661   0.09196  -0.0811   0.8782   0.0516
  -9.000  -0.0322   0.09161   0.08680  -0.0876   0.8593   0.0536
  -8.750  -0.0055   0.08730   0.08233  -0.0943   0.8371   0.0560
  -8.500   0.0111   0.08368   0.07858  -0.0999   0.8141   0.0588
  -8.250   0.0079   0.08112   0.07594  -0.1070   0.7905   0.0612
  -7.750   0.0042   0.07494   0.06955  -0.1134   0.7550   0.0622
  -7.500   0.0327   0.07133   0.06588  -0.1101   0.7398   0.0649
  -7.250   0.0398   0.06877   0.06324  -0.1106   0.7254   0.0665
  -7.000   0.0451   0.06614   0.06053  -0.1115   0.7126   0.0682
  -6.750   0.0502   0.06347   0.05776  -0.1126   0.7012   0.0700
  -6.500   0.0460   0.06142   0.05535  -0.1158   0.6915   0.0749
  -6.000   0.0667   0.05519   0.04906  -0.1139   0.6721   0.0783
  -5.500   0.0847   0.04773   0.04112  -0.1127   0.6561   0.0570
  -5.250   0.0924   0.04420   0.03727  -0.1113   0.6480   0.0534
  -5.000   0.1057   0.04207   0.03489  -0.1100   0.6405   0.0544
  -4.750   0.1185   0.03990   0.03247  -0.1083   0.6322   0.0551
  -4.500   0.1322   0.03733   0.02950  -0.1065   0.6259   0.0539
  -4.250   0.1452   0.03487   0.02666  -0.1041   0.6182   0.0528
  -4.000   0.1615   0.03280   0.02417  -0.1021   0.6117   0.0524
  -3.750   0.1796   0.03158   0.02273  -0.1006   0.6047   0.0538
  -3.500   0.1986   0.03034   0.02121  -0.0991   0.5981   0.0554
  -3.250   0.2189   0.02893   0.01943  -0.0976   0.5923   0.0557
  -3.000   0.2390   0.02763   0.01782  -0.0960   0.5855   0.0558
  -2.750   0.2615   0.02647   0.01630  -0.0948   0.5798   0.0561
  -2.500   0.2842   0.02549   0.01503  -0.0936   0.5736   0.0566
  -2.250   0.3076   0.02477   0.01404  -0.0926   0.5674   0.0586
  -2.000   0.3335   0.02408   0.01303  -0.0920   0.5625   0.0603
  -1.750   0.3577   0.02343   0.01220  -0.0911   0.5566   0.0609
  -1.500   0.3834   0.02285   0.01144  -0.0906   0.5514   0.0615
  -1.250   0.4105   0.02223   0.01067  -0.0904   0.5472   0.0625
  -1.000   0.4350   0.02172   0.01015  -0.0898   0.5422   0.0640
  -0.750   0.4591   0.02137   0.00980  -0.0891   0.5373   0.0660
  -0.500   0.4839   0.02113   0.00950  -0.0886   0.5331   0.0697
  -0.250   0.5087   0.02093   0.00919  -0.0879   0.5290   0.0735
   0.000   0.5312   0.02074   0.00899  -0.0869   0.5243   0.0763
   0.250   0.5560   0.02060   0.00880  -0.0864   0.5202   0.0809
   0.500   0.5843   0.02053   0.00861  -0.0865   0.5168   0.0886
   0.750   0.6133   0.02048   0.00856  -0.0869   0.5136   0.1079
   1.250   0.8115   0.01911   0.00895  -0.1178   0.5030   1.0000
   1.500   0.8351   0.01933   0.00899  -0.1170   0.5002   1.0000
   1.750   0.8558   0.01962   0.00922  -0.1158   0.4968   1.0000
   2.000   0.8760   0.01992   0.00948  -0.1145   0.4932   1.0000
   2.250   0.8975   0.02021   0.00971  -0.1134   0.4902   1.0000
   2.500   0.9198   0.02049   0.00990  -0.1126   0.4875   1.0000
   2.750   0.9433   0.02076   0.01008  -0.1119   0.4852   1.0000
   3.000   0.9650   0.02108   0.01035  -0.1109   0.4826   1.0000
   3.250   0.9827   0.02147   0.01077  -0.1092   0.4792   1.0000
   3.500   1.0021   0.02183   0.01114  -0.1078   0.4761   1.0000
   3.750   1.0230   0.02217   0.01145  -0.1067   0.4734   1.0000
   4.000   1.0452   0.02249   0.01174  -0.1059   0.4711   1.0000
   4.250   1.0692   0.02280   0.01198  -0.1053   0.4690   1.0000
   4.500   1.0867   0.02324   0.01248  -0.1037   0.4661   1.0000
   4.750   1.1020   0.02374   0.01305  -0.1017   0.4630   1.0000
   5.000   1.1195   0.02418   0.01355  -0.1000   0.4600   1.0000
   5.250   1.1391   0.02456   0.01395  -0.0987   0.4574   1.0000
   5.500   1.1612   0.02490   0.01427  -0.0979   0.4550   1.0000
   5.750   1.1866   0.02519   0.01452  -0.0977   0.4527   1.0000
   6.000   1.1951   0.02584   0.01533  -0.0946   0.4491   1.0000
   6.250   1.2072   0.02639   0.01599  -0.0920   0.4456   1.0000
   6.500   1.2237   0.02679   0.01643  -0.0902   0.4422   1.0000
   6.750   1.2457   0.02706   0.01671  -0.0894   0.4392   1.0000
   7.000   1.2708   0.02731   0.01693  -0.0892   0.4365   1.0000
   7.250   1.2713   0.02814   0.01796  -0.0847   0.4325   1.0000
   7.500   1.2800   0.02879   0.01873  -0.0818   0.4291   1.0000
   7.750   1.2945   0.02927   0.01929  -0.0798   0.4260   1.0000
   8.000   1.3151   0.02963   0.01970  -0.0788   0.4235   1.0000
   8.250   1.3417   0.02990   0.01998  -0.0789   0.4214   1.0000
   8.500   1.3332   0.03103   0.02132  -0.0733   0.4176   1.0000
   8.750   1.3278   0.03198   0.02241  -0.0682   0.4139   1.0000
   9.000   1.3341   0.03264   0.02316  -0.0650   0.4108   1.0000
   9.250   1.3531   0.03296   0.02356  -0.0638   0.4080   1.0000
   9.500   1.3840   0.03310   0.02374  -0.0645   0.4057   1.0000
   9.750   1.3471   0.03511   0.02596  -0.0554   0.4013   1.0000
  10.000   1.3300   0.03691   0.02793  -0.0501   0.3971   1.0000
  10.250   1.3380   0.03781   0.02892  -0.0479   0.3939   1.0000
  10.500   1.3636   0.03789   0.02910  -0.0477   0.3915   1.0000
  10.750   1.2744   0.04471   0.03611  -0.0382   0.3833   1.0000
  11.000   1.2645   0.04734   0.03884  -0.0359   0.3785   1.0000
  11.250   1.3025   0.04608   0.03769  -0.0360   0.3765   1.0000
  11.500   1.1587   0.06243   0.05408  -0.0316   0.3578   1.0000
  11.750   1.2051   0.05957   0.05133  -0.0310   0.3590   1.0000
  12.750   1.0740   0.08720   0.07920  -0.0303   0.3178   1.0000
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