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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 500,000
Max Cl/Cd: 105.69 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe596-il-500000.txt
Download as CSV file: xf-goe596-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3437   0.09819   0.09581  -0.0319   1.0000   0.0262
  -9.250  -0.3410   0.09531   0.09295  -0.0326   1.0000   0.0268
  -9.000  -0.3397   0.09231   0.08997  -0.0334   1.0000   0.0275
  -8.750  -0.2945   0.07580   0.07370  -0.0399   1.0000   0.0294
  -8.500  -0.2977   0.07348   0.07143  -0.0373   1.0000   0.0297
  -8.250  -0.2870   0.07036   0.06831  -0.0382   0.9984   0.0300
  -8.000  -0.3824   0.07644   0.07431  -0.0429   0.9969   0.0295
  -7.750  -0.3639   0.07314   0.07100  -0.0450   0.9938   0.0298
  -7.500  -0.3429   0.06987   0.06772  -0.0488   0.9893   0.0302
  -7.250  -0.3185   0.06606   0.06388  -0.0544   0.9850   0.0308
  -7.000  -0.2944   0.06167   0.05945  -0.0609   0.9789   0.0317
  -6.750  -0.2527   0.04983   0.04713  -0.0795   0.9713   0.0353
  -6.500  -0.2379   0.04366   0.04088  -0.0830   0.9636   0.0360
  -6.250  -0.2106   0.04136   0.03854  -0.0855   0.9585   0.0366
  -6.000  -0.1854   0.03911   0.03622  -0.0874   0.9505   0.0373
  -5.750  -0.1581   0.03646   0.03342  -0.0896   0.9429   0.0387
  -5.500  -0.1303   0.03393   0.03026  -0.0903   0.9309   0.0427
  -5.250  -0.1171   0.02831   0.02443  -0.0907   0.9195   0.0440
  -5.000  -0.0933   0.02680   0.02286  -0.0908   0.9096   0.0449
  -4.750  -0.0711   0.02548   0.02143  -0.0903   0.8977   0.0460
  -4.500  -0.0485   0.02409   0.01986  -0.0897   0.8859   0.0479
  -4.250  -0.0200   0.02498   0.02035  -0.0885   0.8746   0.0519
  -4.000  -0.0036   0.02056   0.01562  -0.0878   0.8631   0.0540
  -3.750   0.0199   0.01949   0.01451  -0.0873   0.8502   0.0555
  -3.500   0.0442   0.01870   0.01360  -0.0866   0.8369   0.0581
  -3.250   0.0694   0.01523   0.00922  -0.0843   0.8245   0.0434
  -3.000   0.0951   0.01433   0.00821  -0.0836   0.8101   0.0421
  -2.750   0.1200   0.01326   0.00697  -0.0828   0.7931   0.0417
  -2.500   0.1453   0.01273   0.00626  -0.0820   0.7722   0.0421
  -2.250   0.1706   0.01238   0.00575  -0.0812   0.7490   0.0425
  -2.000   0.1957   0.01189   0.00510  -0.0803   0.7242   0.0427
  -1.750   0.2205   0.01132   0.00440  -0.0795   0.7015   0.0429
  -1.500   0.2448   0.01068   0.00366  -0.0787   0.6811   0.0436
  -1.250   0.2693   0.01030   0.00319  -0.0779   0.6642   0.0444
  -1.000   0.2945   0.01007   0.00289  -0.0772   0.6498   0.0454
  -0.750   0.3201   0.00991   0.00268  -0.0767   0.6375   0.0469
  -0.500   0.3460   0.00981   0.00252  -0.0762   0.6269   0.0490
  -0.250   0.3722   0.00970   0.00237  -0.0757   0.6174   0.0508
   0.000   0.3985   0.00961   0.00222  -0.0753   0.6090   0.0525
   0.250   0.4246   0.00945   0.00204  -0.0748   0.6006   0.0570
   0.500   0.4512   0.00940   0.00195  -0.0744   0.5929   0.0632
   0.750   0.4733   0.00858   0.00194  -0.0736   0.5856   0.3436
   1.000   0.5519   0.00708   0.00210  -0.0847   0.5773   1.0000
   1.250   0.5764   0.00717   0.00212  -0.0839   0.5702   1.0000
   1.500   0.6009   0.00729   0.00216  -0.0831   0.5636   1.0000
   1.750   0.6256   0.00736   0.00220  -0.0824   0.5558   1.0000
   2.000   0.6500   0.00749   0.00224  -0.0816   0.5485   1.0000
   2.250   0.6749   0.00756   0.00230  -0.0809   0.5407   1.0000
   2.500   0.6993   0.00770   0.00236  -0.0801   0.5332   1.0000
   2.750   0.7243   0.00777   0.00243  -0.0794   0.5248   1.0000
   3.000   0.7488   0.00790   0.00251  -0.0787   0.5170   1.0000
   3.250   0.7738   0.00798   0.00259  -0.0780   0.5083   1.0000
   3.500   0.7983   0.00811   0.00268  -0.0773   0.4994   1.0000
   3.750   0.8226   0.00823   0.00276  -0.0765   0.4880   1.0000
   4.000   0.8470   0.00833   0.00285  -0.0757   0.4750   1.0000
   4.250   0.8714   0.00845   0.00295  -0.0749   0.4619   1.0000
   4.500   0.8955   0.00860   0.00305  -0.0741   0.4467   1.0000
   4.750   0.9197   0.00875   0.00318  -0.0734   0.4326   1.0000
   5.000   0.9437   0.00893   0.00332  -0.0726   0.4176   1.0000
   5.250   0.9671   0.00915   0.00348  -0.0717   0.3992   1.0000
   5.500   0.9901   0.00940   0.00366  -0.0708   0.3811   1.0000
   5.750   1.0131   0.00968   0.00387  -0.0699   0.3622   1.0000
   6.000   1.0359   0.00996   0.00411  -0.0690   0.3442   1.0000
   6.250   1.0580   0.01031   0.00437  -0.0680   0.3234   1.0000
   6.500   1.0799   0.01068   0.00466  -0.0670   0.3018   1.0000
   6.750   1.1008   0.01111   0.00498  -0.0659   0.2737   1.0000
   7.000   1.1185   0.01180   0.00541  -0.0643   0.2203   1.0000
   7.250   1.1293   0.01303   0.00618  -0.0617   0.1487   1.0000
   7.500   1.1342   0.01469   0.00728  -0.0582   0.0637   1.0000
   7.750   1.1515   0.01536   0.00792  -0.0565   0.0540   1.0000
   8.000   1.1679   0.01607   0.00863  -0.0547   0.0489   1.0000
   8.250   1.1870   0.01654   0.00917  -0.0533   0.0466   1.0000
   8.500   1.2040   0.01712   0.00978  -0.0516   0.0440   1.0000
   8.750   1.2178   0.01786   0.01055  -0.0494   0.0418   1.0000
   9.000   1.2272   0.01870   0.01145  -0.0465   0.0399   1.0000
   9.250   1.2410   0.01922   0.01205  -0.0443   0.0387   1.0000
   9.500   1.2533   0.01984   0.01272  -0.0419   0.0371   1.0000
   9.750   1.2639   0.02057   0.01349  -0.0394   0.0358   1.0000
  10.000   1.2715   0.02148   0.01445  -0.0367   0.0345   1.0000
  10.250   1.2710   0.02292   0.01595  -0.0331   0.0331   1.0000
  10.500   1.2792   0.02394   0.01705  -0.0309   0.0322   1.0000
  10.750   1.2903   0.02481   0.01800  -0.0291   0.0311   1.0000
  11.000   1.2991   0.02589   0.01915  -0.0273   0.0301   1.0000
  11.250   1.3073   0.02705   0.02036  -0.0256   0.0290   1.0000
  11.500   1.3134   0.02844   0.02180  -0.0238   0.0282   1.0000
  11.750   1.3146   0.03030   0.02371  -0.0220   0.0273   1.0000
  12.000   1.3122   0.03262   0.02610  -0.0200   0.0265   1.0000
  12.250   1.3228   0.03385   0.02743  -0.0191   0.0257   1.0000
  12.500   1.3305   0.03540   0.02908  -0.0182   0.0249   1.0000
  12.750   1.3367   0.03715   0.03090  -0.0174   0.0241   1.0000
  13.000   1.3422   0.03901   0.03283  -0.0166   0.0235   1.0000
  13.250   1.3469   0.04101   0.03488  -0.0160   0.0229   1.0000
  13.500   1.3501   0.04322   0.03714  -0.0155   0.0223   1.0000
  13.750   1.3487   0.04592   0.03988  -0.0143   0.0216   1.0000
  14.000   1.3532   0.04813   0.04221  -0.0140   0.0212   1.0000
  14.250   1.3577   0.05039   0.04460  -0.0140   0.0206   1.0000
  14.500   1.3613   0.05280   0.04711  -0.0139   0.0201   1.0000
  14.750   1.3642   0.05534   0.04974  -0.0140   0.0195   1.0000
  15.000   1.3668   0.05798   0.05247  -0.0143   0.0190   1.0000
  15.250   1.3688   0.06072   0.05530  -0.0146   0.0187   1.0000
  15.500   1.3705   0.06357   0.05820  -0.0151   0.0183   1.0000
  15.750   1.3716   0.06648   0.06118  -0.0154   0.0179   1.0000
  16.000   1.3711   0.06950   0.06424  -0.0151   0.0174   1.0000
  16.250   1.3692   0.07299   0.06788  -0.0158   0.0172   1.0000
  16.500   1.3669   0.07670   0.07174  -0.0168   0.0169   1.0000
  16.750   1.3644   0.08048   0.07567  -0.0179   0.0166   1.0000
  17.000   1.3610   0.08448   0.07981  -0.0190   0.0164   1.0000
  17.250   1.3566   0.08870   0.08418  -0.0205   0.0161   1.0000
  17.500   1.3526   0.09299   0.08859  -0.0222   0.0158   1.0000
  17.750   1.3467   0.09766   0.09341  -0.0240   0.0156   1.0000
  18.000   1.3418   0.10234   0.09820  -0.0263   0.0153   1.0000
  18.250   1.3353   0.10731   0.10329  -0.0286   0.0151   1.0000
  18.500   1.3293   0.11230   0.10840  -0.0310   0.0149   1.0000
  18.750   1.3234   0.11737   0.11357  -0.0336   0.0147   1.0000
  19.000   1.3205   0.12190   0.11815  -0.0361   0.0145   1.0000
  19.250   1.3129   0.12738   0.12375  -0.0390   0.0143   1.0000
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