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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 100,000
Max Cl/Cd: 57.57 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602-il-100000.txt
Download as CSV file: xf-goe602-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3678   0.10260   0.09772  -0.0350   1.0000   0.0946
  -8.750  -0.3854   0.10101   0.09625  -0.0369   1.0000   0.0977
  -8.500  -0.4067   0.09968   0.09506  -0.0378   1.0000   0.0983
  -8.250  -0.3835   0.09450   0.08984  -0.0342   1.0000   0.1028
  -8.000  -0.3849   0.09224   0.08764  -0.0326   1.0000   0.1065
  -7.750  -0.3986   0.09043   0.08593  -0.0313   1.0000   0.1094
  -7.500  -0.4213   0.08908   0.08471  -0.0295   1.0000   0.1109
  -7.250  -0.4465   0.08688   0.08263  -0.0323   1.0000   0.1123
  -7.000  -0.4708   0.08403   0.07971  -0.0381   1.0000   0.1132
  -6.750  -0.4482   0.08060   0.07643  -0.0275   1.0000   0.1172
  -6.500  -0.4499   0.07814   0.07400  -0.0262   1.0000   0.1210
  -6.250  -0.4711   0.07418   0.06982  -0.0369   1.0000   0.1280
  -6.000  -0.4618   0.07070   0.06654  -0.0307   1.0000   0.1302
  -5.750  -0.4568   0.06846   0.06434  -0.0278   1.0000   0.1345
  -5.500  -0.4559   0.06403   0.05973  -0.0324   1.0000   0.1443
  -5.250  -0.4476   0.06176   0.05726  -0.0339   1.0000   0.1568
  -5.000  -0.4411   0.05817   0.05381  -0.0313   1.0000   0.1603
  -4.750  -0.4318   0.05548   0.05104  -0.0313   1.0000   0.1746
  -4.500  -0.4217   0.05315   0.04869  -0.0304   1.0000   0.1897
  -4.250  -0.4102   0.05086   0.04637  -0.0294   1.0000   0.2053
  -4.000  -0.3443   0.03395   0.02694  -0.0414   1.0000   0.0870
  -3.750  -0.3205   0.03217   0.02446  -0.0405   1.0000   0.0845
  -3.500  -0.2985   0.02969   0.02158  -0.0401   1.0000   0.0855
  -3.250  -0.2608   0.02764   0.01903  -0.0420   0.9958   0.0853
  -3.000  -0.2206   0.02596   0.01724  -0.0450   0.9894   0.0906
  -2.750  -0.1765   0.02490   0.01586  -0.0480   0.9833   0.0949
  -2.500  -0.1372   0.02392   0.01460  -0.0500   0.9752   0.0995
  -2.250  -0.0967   0.02313   0.01386  -0.0527   0.9680   0.1096
  -2.000  -0.0576   0.02230   0.01311  -0.0549   0.9600   0.1194
  -1.750  -0.0211   0.02162   0.01248  -0.0566   0.9514   0.1417
  -1.500   0.0122   0.01917   0.01217  -0.0580   0.9455   0.5468
  -1.250   0.0735   0.01825   0.01212  -0.0632   0.9413   1.0000
  -1.000   0.1139   0.01843   0.01197  -0.0658   0.9314   1.0000
  -0.750   0.1507   0.01858   0.01187  -0.0678   0.9206   1.0000
  -0.500   0.1941   0.01870   0.01178  -0.0709   0.9121   1.0000
  -0.250   0.2347   0.01875   0.01164  -0.0734   0.9026   1.0000
   0.000   0.2697   0.01881   0.01157  -0.0748   0.8914   1.0000
   0.250   0.3211   0.01867   0.01129  -0.0791   0.8857   1.0000
   0.500   0.3550   0.01863   0.01116  -0.0801   0.8739   1.0000
   0.750   0.3905   0.01856   0.01101  -0.0814   0.8628   1.0000
   1.000   0.4440   0.01814   0.01054  -0.0858   0.8576   1.0000
   1.250   0.4765   0.01802   0.01037  -0.0863   0.8453   1.0000
   1.500   0.5108   0.01783   0.01016  -0.0870   0.8337   1.0000
   1.750   0.5481   0.01755   0.00987  -0.0882   0.8231   1.0000
   2.000   0.5917   0.01706   0.00937  -0.0903   0.8145   1.0000
   2.250   0.6235   0.01684   0.00914  -0.0904   0.8011   1.0000
   2.500   0.6557   0.01661   0.00893  -0.0906   0.7874   1.0000
   2.750   0.6879   0.01639   0.00870  -0.0907   0.7732   1.0000
   3.000   0.7196   0.01621   0.00851  -0.0907   0.7583   1.0000
   3.250   0.7508   0.01608   0.00838  -0.0906   0.7429   1.0000
   3.500   0.7784   0.01609   0.00839  -0.0900   0.7259   1.0000
   3.750   0.8044   0.01618   0.00848  -0.0892   0.7078   1.0000
   4.000   0.8315   0.01625   0.00854  -0.0885   0.6895   1.0000
   4.250   0.8595   0.01632   0.00859  -0.0880   0.6712   1.0000
   4.500   0.8834   0.01650   0.00877  -0.0868   0.6510   1.0000
   4.750   0.9077   0.01669   0.00896  -0.0857   0.6310   1.0000
   5.000   0.9338   0.01689   0.00912  -0.0849   0.6121   1.0000
   5.250   0.9558   0.01719   0.00950  -0.0835   0.5923   1.0000
   5.500   0.9789   0.01746   0.00979  -0.0823   0.5722   1.0000
   5.750   1.0012   0.01771   0.01003  -0.0808   0.5505   1.0000
   6.000   1.0203   0.01786   0.01013  -0.0787   0.5228   1.0000
   6.250   1.0361   0.01802   0.01029  -0.0760   0.4911   1.0000
   6.500   1.0530   0.01829   0.01054  -0.0737   0.4622   1.0000
   6.750   1.0695   0.01862   0.01087  -0.0714   0.4334   1.0000
   7.000   1.0842   0.01898   0.01123  -0.0689   0.4010   1.0000
   7.250   1.0973   0.01943   0.01162  -0.0661   0.3652   1.0000
   7.500   1.1074   0.02001   0.01212  -0.0629   0.3163   1.0000
   7.750   1.1133   0.02100   0.01277  -0.0592   0.2501   1.0000
   8.000   1.1125   0.02276   0.01390  -0.0550   0.1519   1.0000
   8.250   1.1069   0.02513   0.01562  -0.0503   0.0891   1.0000
   8.500   1.1089   0.02679   0.01719  -0.0464   0.0704   1.0000
   8.750   1.1134   0.02824   0.01862  -0.0430   0.0617   1.0000
   9.000   1.1197   0.02957   0.02007  -0.0400   0.0568   1.0000
   9.250   1.1236   0.03110   0.02164  -0.0369   0.0538   1.0000
   9.500   1.1259   0.03288   0.02348  -0.0338   0.0518   1.0000
   9.750   1.1338   0.03454   0.02526  -0.0314   0.0503   1.0000
  10.000   1.1452   0.03624   0.02704  -0.0294   0.0481   1.0000
  10.250   1.1580   0.03798   0.02880  -0.0278   0.0454   1.0000
  10.500   1.1833   0.04034   0.03109  -0.0274   0.0434   1.0000
  10.750   1.2363   0.04441   0.03528  -0.0303   0.0426   1.0000
  11.000   1.2703   0.04850   0.03972  -0.0315   0.0426   1.0000
  11.250   1.2864   0.05190   0.04350  -0.0303   0.0428   1.0000
  11.500   1.2925   0.05546   0.04741  -0.0282   0.0428   1.0000
  11.750   1.2914   0.05881   0.05109  -0.0254   0.0428   1.0000
  12.000   1.2849   0.06227   0.05486  -0.0224   0.0427   1.0000
  12.250   1.2755   0.06493   0.05781  -0.0193   0.0429   1.0000
  12.500   1.2628   0.06783   0.06099  -0.0165   0.0431   1.0000
  12.750   1.2463   0.07081   0.06427  -0.0141   0.0435   1.0000
  13.000   1.2239   0.07453   0.06834  -0.0125   0.0440   1.0000
  13.250   1.1856   0.07982   0.07405  -0.0122   0.0451   1.0000
  13.500   1.1464   0.08680   0.08139  -0.0141   0.0464   1.0000
  13.750   1.1137   0.09422   0.08906  -0.0174   0.0474   1.0000
  14.000   1.0817   0.10267   0.09771  -0.0221   0.0486   1.0000
  14.250   1.0526   0.11176   0.10694  -0.0276   0.0497   1.0000
  14.500   1.0280   0.12114   0.11637  -0.0334   0.0508   1.0000
  14.750   1.0120   0.12964   0.12490  -0.0381   0.0517   1.0000
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