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=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 200,000
Max Cl/Cd: 61.19 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe604-il-200000-n5.txt
Download as CSV file: xf-goe604-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6124   0.05568   0.05112  -0.0872   1.0000   0.0330
 -13.250  -0.6406   0.04988   0.04518  -0.0908   1.0000   0.0331
 -13.000  -0.6666   0.04571   0.04088  -0.0922   0.9998   0.0332
 -12.750  -0.6598   0.04183   0.03682  -0.0975   0.9872   0.0336
 -12.500  -0.6509   0.03903   0.03383  -0.1010   0.9749   0.0343
 -12.250  -0.6408   0.03647   0.03103  -0.1033   0.9624   0.0350
 -12.000  -0.6295   0.03418   0.02845  -0.1046   0.9489   0.0358
 -11.750  -0.6157   0.03208   0.02600  -0.1053   0.9345   0.0366
 -11.500  -0.5902   0.03073   0.02460  -0.1065   0.9214   0.0372
 -11.250  -0.5668   0.02971   0.02352  -0.1069   0.9052   0.0380
 -11.000  -0.5455   0.02863   0.02230  -0.1069   0.8870   0.0389
 -10.750  -0.5261   0.02756   0.02102  -0.1064   0.8659   0.0399
 -10.500  -0.5076   0.02650   0.01971  -0.1054   0.8425   0.0408
 -10.250  -0.4891   0.02555   0.01847  -0.1043   0.8174   0.0417
 -10.000  -0.4693   0.02479   0.01763  -0.1032   0.7928   0.0425
  -9.750  -0.4503   0.02416   0.01687  -0.1019   0.7689   0.0434
  -9.500  -0.4314   0.02357   0.01610  -0.1006   0.7466   0.0444
  -9.250  -0.4124   0.02296   0.01528  -0.0991   0.7264   0.0455
  -9.000  -0.3930   0.02237   0.01447  -0.0977   0.7087   0.0465
  -8.750  -0.3731   0.02179   0.01372  -0.0964   0.6935   0.0475
  -8.500  -0.3530   0.02126   0.01313  -0.0951   0.6802   0.0486
  -8.250  -0.3322   0.02080   0.01256  -0.0939   0.6678   0.0498
  -8.000  -0.3109   0.02033   0.01197  -0.0928   0.6565   0.0511
  -7.750  -0.2893   0.01990   0.01138  -0.0916   0.6467   0.0524
  -7.500  -0.2673   0.01944   0.01082  -0.0906   0.6371   0.0537
  -7.000  -0.2234   0.01862   0.00988  -0.0885   0.6201   0.0571
  -6.750  -0.2005   0.01828   0.00942  -0.0875   0.6123   0.0591
  -6.500  -0.1778   0.01790   0.00897  -0.0865   0.6051   0.0611
  -6.250  -0.1549   0.01754   0.00856  -0.0856   0.5973   0.0634
  -5.750  -0.1080   0.01691   0.00779  -0.0838   0.5831   0.0701
  -5.500  -0.0842   0.01662   0.00743  -0.0829   0.5760   0.0747
  -5.250  -0.0605   0.01633   0.00709  -0.0821   0.5700   0.0804
  -5.000  -0.0363   0.01602   0.00681  -0.0813   0.5635   0.0892
  -4.750  -0.0122   0.01575   0.00660  -0.0806   0.5575   0.1051
  -4.500   0.0127   0.01559   0.00646  -0.0799   0.5522   0.1269
  -4.250   0.0385   0.01547   0.00634  -0.0794   0.5462   0.1439
  -4.000   0.0639   0.01537   0.00621  -0.0788   0.5403   0.1567
  -3.750   0.0895   0.01531   0.00606  -0.0782   0.5352   0.1678
  -3.500   0.1151   0.01520   0.00596  -0.0776   0.5299   0.1786
  -3.250   0.1405   0.01510   0.00586  -0.0771   0.5243   0.1888
  -3.000   0.1661   0.01504   0.00574  -0.0765   0.5190   0.1995
  -2.750   0.1912   0.01495   0.00566  -0.0759   0.5140   0.2112
  -2.500   0.2166   0.01486   0.00560  -0.0753   0.5082   0.2250
  -2.250   0.2417   0.01478   0.00555  -0.0747   0.5029   0.2418
  -2.000   0.2666   0.01473   0.00549  -0.0740   0.4985   0.2612
  -1.750   0.2919   0.01464   0.00547  -0.0734   0.4933   0.2796
  -1.500   0.3171   0.01457   0.00543  -0.0728   0.4879   0.2970
  -1.250   0.3419   0.01453   0.00537  -0.0721   0.4828   0.3160
  -1.000   0.3666   0.01448   0.00535  -0.0714   0.4779   0.3373
  -0.750   0.3913   0.01442   0.00535  -0.0707   0.4721   0.3610
  -0.250   0.4390   0.01430   0.00533  -0.0691   0.4622   0.4226
   0.000   0.4625   0.01419   0.00539  -0.0682   0.4570   0.4640
   0.250   0.4849   0.01406   0.00543  -0.0670   0.4518   0.5169
   0.500   0.5059   0.01391   0.00547  -0.0656   0.4473   0.5877
   0.750   0.5265   0.01371   0.00558  -0.0639   0.4427   0.6782
   1.000   0.5528   0.01356   0.00576  -0.0632   0.4373   0.7850
   1.250   0.6081   0.01368   0.00600  -0.0683   0.4311   0.8865
   1.500   0.6609   0.01389   0.00616  -0.0733   0.4250   0.9334
   1.750   0.7065   0.01409   0.00631  -0.0769   0.4188   0.9594
   2.000   0.7478   0.01432   0.00643  -0.0797   0.4137   0.9798
   2.250   0.7931   0.01454   0.00658  -0.0834   0.4087   0.9947
   2.500   0.8265   0.01472   0.00672  -0.0847   0.4037   1.0000
   2.750   0.8455   0.01489   0.00682  -0.0831   0.3996   1.0000
   3.000   0.8643   0.01508   0.00693  -0.0815   0.3960   1.0000
   3.250   0.8838   0.01527   0.00708  -0.0800   0.3919   1.0000
   3.500   0.9031   0.01545   0.00724  -0.0785   0.3874   1.0000
   3.750   0.9218   0.01565   0.00738  -0.0768   0.3829   1.0000
   4.000   0.9403   0.01587   0.00752  -0.0752   0.3789   1.0000
   4.250   0.9595   0.01608   0.00772  -0.0737   0.3746   1.0000
   4.500   0.9784   0.01629   0.00792  -0.0721   0.3702   1.0000
   4.750   0.9971   0.01652   0.00811  -0.0705   0.3665   1.0000
   5.000   1.0157   0.01677   0.00831  -0.0689   0.3635   1.0000
   5.250   1.0347   0.01704   0.00853  -0.0674   0.3606   1.0000
   5.500   1.0537   0.01728   0.00880  -0.0659   0.3574   1.0000
   5.750   1.0720   0.01754   0.00907  -0.0643   0.3540   1.0000
   6.000   1.0898   0.01781   0.00932  -0.0627   0.3507   1.0000
   6.250   1.1075   0.01810   0.00958  -0.0610   0.3479   1.0000
   6.500   1.1248   0.01841   0.00984  -0.0593   0.3453   1.0000
   6.750   1.1410   0.01870   0.01017  -0.0575   0.3425   1.0000
   7.000   1.1563   0.01899   0.01051  -0.0554   0.3393   1.0000
   7.250   1.1717   0.01931   0.01085  -0.0535   0.3361   1.0000
   7.500   1.1872   0.01965   0.01118  -0.0516   0.3331   1.0000
   7.750   1.2030   0.02001   0.01152  -0.0499   0.3304   1.0000
   8.000   1.2193   0.02040   0.01190  -0.0483   0.3276   1.0000
   8.250   1.2346   0.02080   0.01237  -0.0466   0.3248   1.0000
   8.500   1.2503   0.02123   0.01286  -0.0451   0.3222   1.0000
   8.750   1.2655   0.02167   0.01335  -0.0435   0.3195   1.0000
   9.000   1.2798   0.02215   0.01384  -0.0419   0.3164   1.0000
   9.250   1.2943   0.02265   0.01432  -0.0403   0.3134   1.0000
   9.500   1.3086   0.02320   0.01489  -0.0388   0.3105   1.0000
   9.750   1.3217   0.02380   0.01559  -0.0373   0.3077   1.0000
  10.000   1.3343   0.02444   0.01631  -0.0358   0.3047   1.0000
  10.250   1.3463   0.02512   0.01704  -0.0343   0.3015   1.0000
  10.500   1.3580   0.02584   0.01777  -0.0328   0.2983   1.0000
  10.750   1.3711   0.02655   0.01847  -0.0316   0.2955   1.0000
  11.000   1.3800   0.02749   0.01955  -0.0301   0.2921   1.0000
  11.250   1.3886   0.02850   0.02066  -0.0287   0.2883   1.0000
  11.500   1.3971   0.02955   0.02176  -0.0274   0.2846   1.0000
  11.750   1.4058   0.03062   0.02285  -0.0262   0.2813   1.0000
  12.000   1.4135   0.03184   0.02415  -0.0251   0.2779   1.0000
  12.250   1.4186   0.03331   0.02576  -0.0241   0.2737   1.0000
  12.500   1.4231   0.03486   0.02738  -0.0231   0.2693   1.0000
  12.750   1.4281   0.03641   0.02894  -0.0222   0.2654   1.0000
  13.000   1.4301   0.03835   0.03101  -0.0214   0.2608   1.0000
  13.250   1.4299   0.04054   0.03330  -0.0208   0.2555   1.0000
  13.500   1.4307   0.04268   0.03546  -0.0202   0.2506   1.0000
  13.750   1.4278   0.04536   0.03827  -0.0199   0.2447   1.0000
  14.000   1.4244   0.04810   0.04107  -0.0195   0.2387   1.0000
  14.250   1.4198   0.05107   0.04411  -0.0194   0.2327   1.0000
  14.500   1.4127   0.05440   0.04751  -0.0193   0.2259   1.0000
  14.750   1.4062   0.05771   0.05087  -0.0193   0.2198   1.0000
  15.000   1.3981   0.06131   0.05453  -0.0195   0.2132   1.0000
  15.250   1.3918   0.06474   0.05797  -0.0197   0.2081   1.0000
  15.500   1.3848   0.06835   0.06165  -0.0200   0.2027   1.0000
  15.750   1.3789   0.07182   0.06511  -0.0203   0.1978   1.0000
  16.000   1.3745   0.07519   0.06851  -0.0206   0.1935   1.0000
  16.250   1.3696   0.07868   0.07206  -0.0211   0.1894   1.0000
  16.500   1.3680   0.08171   0.07509  -0.0214   0.1857   1.0000
  16.750   1.3685   0.08446   0.07782  -0.0218   0.1824   1.0000
  17.000   1.3661   0.08775   0.08121  -0.0223   0.1795   1.0000
  17.250   1.3642   0.09099   0.08451  -0.0229   0.1766   1.0000
  17.500   1.3657   0.09371   0.08725  -0.0234   0.1736   1.0000
  17.750   1.3721   0.09569   0.08920  -0.0237   0.1709   1.0000
  18.000   1.3761   0.09807   0.09162  -0.0241   0.1688   1.0000
  18.250   1.3735   0.10151   0.09519  -0.0250   0.1667   1.0000
  18.500   1.3719   0.10483   0.09861  -0.0259   0.1645   1.0000
<< Back to GOE 604 AIRFOIL (goe604-il)

Polar data table (+)

Polar graphs


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