Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 500,000
Max Cl/Cd: 87.75 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe604-il-500000.txt
Download as CSV file: xf-goe604-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 604 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6308   0.07578   0.07268  -0.0757   1.0000   0.0290
 -15.250  -0.6854   0.06380   0.06044  -0.0848   1.0000   0.0290
 -15.000  -0.7224   0.05517   0.05161  -0.0912   1.0000   0.0289
 -14.750  -0.7452   0.04908   0.04533  -0.0959   1.0000   0.0290
 -14.500  -0.7674   0.04393   0.03999  -0.0993   1.0000   0.0291
 -14.250  -0.7865   0.04033   0.03622  -0.1005   1.0000   0.0293
 -14.000  -0.8064   0.03775   0.03350  -0.0993   1.0000   0.0294
 -13.750  -0.8305   0.03599   0.03165  -0.0956   1.0000   0.0295
 -13.500  -0.8362   0.03398   0.02958  -0.0940   0.9985   0.0298
 -13.250  -0.8104   0.03245   0.02804  -0.0964   0.9940   0.0304
 -13.000  -0.7874   0.03117   0.02671  -0.0980   0.9878   0.0309
 -12.750  -0.7625   0.02983   0.02527  -0.0998   0.9823   0.0315
 -12.500  -0.7403   0.02848   0.02379  -0.1006   0.9752   0.0321
 -12.250  -0.7130   0.02702   0.02216  -0.1023   0.9697   0.0328
 -12.000  -0.6857   0.02592   0.02083  -0.1037   0.9627   0.0335
 -11.750  -0.6567   0.02418   0.01905  -0.1054   0.9553   0.0344
 -11.500  -0.6267   0.02336   0.01823  -0.1065   0.9454   0.0351
 -11.250  -0.5965   0.02253   0.01732  -0.1076   0.9341   0.0359
 -11.000  -0.5715   0.02176   0.01642  -0.1076   0.9188   0.0367
 -10.750  -0.5510   0.02105   0.01556  -0.1065   0.8995   0.0374
 -10.500  -0.5316   0.02053   0.01483  -0.1050   0.8765   0.0381
 -10.250  -0.5135   0.01956   0.01374  -0.1036   0.8504   0.0389
 -10.000  -0.4944   0.01904   0.01313  -0.1020   0.8214   0.0397
  -9.750  -0.4756   0.01868   0.01261  -0.1003   0.7899   0.0405
  -9.500  -0.4569   0.01831   0.01205  -0.0986   0.7586   0.0413
  -9.250  -0.4377   0.01796   0.01150  -0.0969   0.7315   0.0421
  -9.000  -0.4174   0.01764   0.01099  -0.0954   0.7089   0.0429
  -8.750  -0.3980   0.01706   0.01028  -0.0939   0.6907   0.0439
  -8.500  -0.3775   0.01662   0.00977  -0.0926   0.6751   0.0449
  -8.250  -0.3558   0.01630   0.00936  -0.0914   0.6616   0.0459
  -8.000  -0.3332   0.01596   0.00894  -0.0903   0.6497   0.0470
  -7.750  -0.3101   0.01568   0.00853  -0.0893   0.6393   0.0481
  -7.500  -0.2872   0.01534   0.00809  -0.0882   0.6291   0.0492
  -7.250  -0.2657   0.01485   0.00758  -0.0871   0.6203   0.0507
  -7.000  -0.2422   0.01456   0.00724  -0.0861   0.6114   0.0521
  -6.750  -0.2183   0.01431   0.00690  -0.0852   0.6036   0.0537
  -6.500  -0.1933   0.01409   0.00661  -0.0845   0.5961   0.0551
  -6.250  -0.1714   0.01365   0.00615  -0.0833   0.5893   0.0573
  -6.000  -0.1466   0.01340   0.00587  -0.0826   0.5830   0.0598
  -5.750  -0.1214   0.01319   0.00560  -0.0819   0.5765   0.0622
  -5.500  -0.0981   0.01286   0.00524  -0.0809   0.5706   0.0657
  -5.250  -0.0725   0.01266   0.00500  -0.0803   0.5652   0.0697
  -5.000  -0.0482   0.01232   0.00469  -0.0795   0.5595   0.0762
  -4.750  -0.0239   0.01205   0.00442  -0.0787   0.5539   0.0868
  -4.500   0.0000   0.01172   0.00425  -0.0779   0.5486   0.1165
  -4.250   0.0263   0.01157   0.00419  -0.0774   0.5432   0.1438
  -4.000   0.0527   0.01150   0.00411  -0.0769   0.5379   0.1578
  -3.750   0.0792   0.01151   0.00405  -0.0765   0.5328   0.1676
  -3.500   0.1056   0.01140   0.00398  -0.0760   0.5281   0.1774
  -3.250   0.1323   0.01133   0.00389  -0.0756   0.5229   0.1851
  -3.000   0.1582   0.01127   0.00381  -0.0751   0.5176   0.1938
  -2.750   0.1846   0.01125   0.00375  -0.0746   0.5125   0.2018
  -2.500   0.2109   0.01114   0.00369  -0.0741   0.5074   0.2119
  -2.250   0.2370   0.01107   0.00362  -0.0736   0.5022   0.2226
  -2.000   0.2627   0.01104   0.00358  -0.0731   0.4972   0.2375
  -1.750   0.2887   0.01095   0.00356  -0.0726   0.4926   0.2571
  -1.500   0.3144   0.01083   0.00354  -0.0721   0.4874   0.2827
  -1.250   0.3396   0.01075   0.00352  -0.0714   0.4823   0.3133
  -1.000   0.3645   0.01070   0.00352  -0.0708   0.4773   0.3454
  -0.750   0.3899   0.01057   0.00351  -0.0702   0.4723   0.3767
  -0.500   0.4147   0.01048   0.00350  -0.0695   0.4668   0.4102
  -0.250   0.4384   0.01042   0.00350  -0.0686   0.4614   0.4517
   0.000   0.4620   0.01023   0.00352  -0.0677   0.4562   0.5091
   0.250   0.4833   0.01001   0.00355  -0.0663   0.4508   0.5895
   0.500   0.5019   0.00977   0.00360  -0.0643   0.4457   0.6891
   0.750   0.5210   0.00954   0.00371  -0.0622   0.4409   0.7959
   1.000   0.5553   0.00946   0.00388  -0.0630   0.4349   0.8916
   1.250   0.6129   0.00970   0.00407  -0.0690   0.4280   0.9383
   1.500   0.6623   0.00989   0.00422  -0.0734   0.4217   0.9571
   1.750   0.7018   0.01007   0.00434  -0.0757   0.4154   0.9698
   2.000   0.7389   0.01032   0.00447  -0.0776   0.4088   0.9802
   2.250   0.7845   0.01044   0.00456  -0.0813   0.4019   0.9860
   2.500   0.8279   0.01065   0.00468  -0.0846   0.3953   0.9931
   2.750   0.8781   0.01083   0.00479  -0.0893   0.3896   0.9987
   3.000   0.9068   0.01093   0.00487  -0.0896   0.3847   1.0000
   3.250   0.9252   0.01107   0.00496  -0.0879   0.3806   1.0000
   3.500   0.9427   0.01127   0.00508  -0.0860   0.3763   1.0000
   3.750   0.9625   0.01137   0.00519  -0.0845   0.3727   1.0000
   4.000   0.9818   0.01149   0.00530  -0.0829   0.3687   1.0000
   4.250   1.0003   0.01166   0.00542  -0.0811   0.3646   1.0000
   4.500   1.0182   0.01188   0.00558  -0.0793   0.3609   1.0000
   4.750   1.0376   0.01205   0.00574  -0.0777   0.3579   1.0000
   5.000   1.0576   0.01219   0.00589  -0.0763   0.3551   1.0000
   5.250   1.0772   0.01235   0.00605  -0.0747   0.3521   1.0000
   5.500   1.0962   0.01254   0.00622  -0.0731   0.3492   1.0000
   5.750   1.1146   0.01276   0.00640  -0.0714   0.3464   1.0000
   6.000   1.1330   0.01306   0.00664  -0.0698   0.3432   1.0000
   6.250   1.1527   0.01320   0.00683  -0.0683   0.3411   1.0000
   6.500   1.1718   0.01337   0.00703  -0.0668   0.3384   1.0000
   6.750   1.1890   0.01355   0.00722  -0.0649   0.3355   1.0000
   7.000   1.2048   0.01376   0.00741  -0.0627   0.3327   1.0000
   7.250   1.2205   0.01401   0.00764  -0.0606   0.3302   1.0000
   7.500   1.2376   0.01434   0.00793  -0.0589   0.3272   1.0000
   7.750   1.2551   0.01453   0.00817  -0.0571   0.3253   1.0000
   8.000   1.2726   0.01474   0.00843  -0.0555   0.3229   1.0000
   8.250   1.2902   0.01497   0.00869  -0.0539   0.3203   1.0000
   8.500   1.3071   0.01524   0.00897  -0.0522   0.3172   1.0000
   8.750   1.3235   0.01557   0.00928  -0.0506   0.3144   1.0000
   9.000   1.3407   0.01598   0.00966  -0.0491   0.3115   1.0000
   9.250   1.3585   0.01627   0.01002  -0.0478   0.3094   1.0000
   9.500   1.3760   0.01657   0.01038  -0.0465   0.3069   1.0000
   9.750   1.3933   0.01691   0.01077  -0.0452   0.3043   1.0000
  10.000   1.4099   0.01729   0.01118  -0.0438   0.3016   1.0000
  10.250   1.4253   0.01775   0.01163  -0.0424   0.2987   1.0000
  10.500   1.4405   0.01829   0.01216  -0.0410   0.2955   1.0000
  10.750   1.4567   0.01872   0.01268  -0.0398   0.2930   1.0000
  11.000   1.4728   0.01919   0.01322  -0.0387   0.2900   1.0000
  11.250   1.4875   0.01974   0.01381  -0.0375   0.2865   1.0000
  11.500   1.5007   0.02040   0.01449  -0.0362   0.2831   1.0000
  11.750   1.5123   0.02119   0.01529  -0.0348   0.2792   1.0000
  12.000   1.5270   0.02184   0.01604  -0.0339   0.2750   1.0000
  12.250   1.5383   0.02272   0.01695  -0.0327   0.2695   1.0000
  12.500   1.5453   0.02391   0.01814  -0.0314   0.2639   1.0000
  12.750   1.5577   0.02486   0.01918  -0.0306   0.2575   1.0000
  13.000   1.5620   0.02639   0.02071  -0.0294   0.2505   1.0000
  13.250   1.5704   0.02775   0.02213  -0.0286   0.2423   1.0000
  13.500   1.5705   0.02982   0.02420  -0.0276   0.2329   1.0000
  13.750   1.5682   0.03221   0.02659  -0.0267   0.2224   1.0000
  14.000   1.5654   0.03475   0.02914  -0.0260   0.2121   1.0000
  14.250   1.5556   0.03802   0.03240  -0.0252   0.2021   1.0000
  14.500   1.5477   0.04120   0.03559  -0.0246   0.1959   1.0000
  14.750   1.5401   0.04441   0.03882  -0.0242   0.1901   1.0000
  15.000   1.5334   0.04759   0.04204  -0.0238   0.1857   1.0000
  15.250   1.5244   0.05104   0.04551  -0.0235   0.1822   1.0000
  15.500   1.5208   0.05398   0.04849  -0.0233   0.1791   1.0000
  15.750   1.5200   0.05670   0.05127  -0.0232   0.1766   1.0000
  16.000   1.5150   0.05987   0.05450  -0.0232   0.1736   1.0000
  16.250   1.5109   0.06297   0.05762  -0.0232   0.1712   1.0000
  16.500   1.5046   0.06630   0.06095  -0.0232   0.1681   1.0000
  16.750   1.5051   0.06900   0.06372  -0.0234   0.1660   1.0000
  17.000   1.5066   0.07159   0.06639  -0.0236   0.1643   1.0000
  17.250   1.5063   0.07441   0.06929  -0.0238   0.1622   1.0000
  17.500   1.5036   0.07751   0.07243  -0.0241   0.1597   1.0000
  17.750   1.5044   0.08019   0.07514  -0.0244   0.1582   1.0000
  18.000   1.5028   0.08308   0.07804  -0.0246   0.1555   1.0000
  18.250   1.5068   0.08532   0.08031  -0.0248   0.1536   1.0000
  18.500   1.5055   0.08844   0.08355  -0.0254   0.1521   1.0000
  18.750   1.5042   0.09156   0.08677  -0.0261   0.1501   1.0000
  19.000   1.5033   0.09462   0.08989  -0.0267   0.1481   1.0000
<< Back to GOE 604 AIRFOIL (goe604-il)

Polar data table (+)

Polar graphs


<< Back to GOE 604 AIRFOIL (goe604-il)