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GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 777 AIRFOIL (goe777-il)
Reynolds number: 50,000
Max Cl/Cd: 8.14 at α=0.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe777-il-50000-n5.txt
Download as CSV file: xf-goe777-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 777 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.1955   0.12689   0.11914  -0.0554   0.7417   0.0898
 -13.000  -0.1989   0.12208   0.11428  -0.0580   0.7361   0.0902
 -12.750  -0.2049   0.11681   0.10895  -0.0608   0.7316   0.0906
 -12.500  -0.2028   0.11265   0.10478  -0.0629   0.7257   0.0912
 -12.250  -0.2073   0.10729   0.09942  -0.0658   0.7208   0.0912
 -12.000  -0.2087   0.10268   0.09478  -0.0681   0.7158   0.0918
 -11.750  -0.2087   0.09857   0.09062  -0.0699   0.7113   0.0929
 -11.500  -0.2198   0.09223   0.08423  -0.0736   0.7082   0.0940
 -11.250  -0.3062   0.07397   0.06580  -0.0884   0.7093   0.0927
 -11.000  -0.3616   0.06570   0.05720  -0.0934   0.7067   0.0923
 -10.750  -0.3793   0.06240   0.05375  -0.0932   0.7016   0.0930
 -10.500  -0.3913   0.05964   0.05078  -0.0921   0.6968   0.0940
 -10.250  -0.3986   0.05693   0.04779  -0.0909   0.6923   0.0951
 -10.000  -0.4026   0.05432   0.04484  -0.0895   0.6884   0.0965
  -9.750  -0.4050   0.05182   0.04187  -0.0878   0.6848   0.0984
  -9.500  -0.3990   0.04984   0.03964  -0.0866   0.6801   0.1005
  -9.250  -0.3811   0.04865   0.03843  -0.0861   0.6757   0.1029
  -9.000  -0.3670   0.04717   0.03676  -0.0852   0.6718   0.1055
  -8.750  -0.3546   0.04553   0.03470  -0.0840   0.6685   0.1086
  -8.500  -0.3350   0.04427   0.03332  -0.0833   0.6653   0.1116
  -8.250  -0.3147   0.04329   0.03224  -0.0827   0.6619   0.1152
  -8.000  -0.2975   0.04231   0.03103  -0.0818   0.6576   0.1193
  -7.750  -0.2764   0.04148   0.03018  -0.0813   0.6534   0.1232
  -7.500  -0.2548   0.04075   0.02938  -0.0807   0.6497   0.1278
  -7.250  -0.2332   0.03996   0.02837  -0.0800   0.6466   0.1331
  -7.000  -0.2090   0.03932   0.02777  -0.0796   0.6439   0.1382
  -6.750  -0.1851   0.03870   0.02692  -0.0789   0.6416   0.1447
  -6.500  -0.1651   0.03846   0.02684  -0.0784   0.6376   0.1500
  -6.250  -0.1452   0.03828   0.02662  -0.0776   0.6335   0.1566
  -6.000  -0.1243   0.03800   0.02637  -0.0768   0.6298   0.1630
  -5.750  -0.1028   0.03773   0.02608  -0.0760   0.6265   0.1707
  -5.500  -0.0807   0.03741   0.02576  -0.0752   0.6238   0.1787
  -5.250  -0.0577   0.03707   0.02536  -0.0744   0.6213   0.1889
  -5.000  -0.0400   0.03698   0.02537  -0.0732   0.6180   0.1990
  -4.750  -0.0292   0.03736   0.02588  -0.0716   0.6132   0.2109
  -4.500  -0.0154   0.03746   0.02611  -0.0701   0.6089   0.2280
  -4.250   0.0005   0.03730   0.02615  -0.0687   0.6053   0.2556
  -4.000   0.0186   0.03694   0.02600  -0.0673   0.6021   0.3043
  -3.750   0.0388   0.03644   0.02575  -0.0659   0.5993   0.3706
  -3.500   0.0422   0.03717   0.02681  -0.0631   0.5935   0.4185
  -3.250   0.0475   0.03787   0.02786  -0.0602   0.5873   0.4700
  -3.000   0.0652   0.03807   0.02822  -0.0579   0.5828   0.5325
  -2.750   0.0887   0.03807   0.02818  -0.0562   0.5794   0.5859
  -2.500   0.1156   0.03797   0.02801  -0.0546   0.5767   0.6310
  -2.250   0.0998   0.04018   0.03041  -0.0506   0.5664   0.6527
  -2.000   0.1150   0.04066   0.03094  -0.0480   0.5615   0.6937
  -1.750   0.1379   0.04076   0.03107  -0.0453   0.5582   0.7396
  -1.500   0.1646   0.04078   0.03107  -0.0429   0.5556   0.7821
  -1.250   0.1415   0.04350   0.03397  -0.0386   0.5445   0.8021
  -1.000   0.1623   0.04413   0.03458  -0.0369   0.5393   0.8340
  -0.750   0.1998   0.04418   0.03450  -0.0371   0.5362   0.8627
  -0.500   0.2459   0.04401   0.03412  -0.0388   0.5338   0.8839
  -0.250   0.2224   0.04761   0.03790  -0.0365   0.5203   0.9079
   0.000   0.2684   0.04795   0.03808  -0.0395   0.5161   0.9271
   0.250   0.3260   0.04782   0.03773  -0.0438   0.5136   0.9438
   0.500   0.3870   0.04755   0.03722  -0.0485   0.5114   0.9586
   1.000   0.4063   0.05225   0.04191  -0.0519   0.4927   1.0000
   1.250   0.4172   0.05175   0.04123  -0.0493   0.4904   1.0000
   1.750   0.3555   0.05695   0.04628  -0.0404   0.4718   1.0000
   2.000   0.3261   0.06085   0.05015  -0.0379   0.4605   1.0000
   2.250   0.3411   0.06179   0.05093  -0.0372   0.4559   1.0000
   2.500   0.3659   0.06208   0.05105  -0.0369   0.4533   1.0000
   3.000   0.3575   0.06760   0.05645  -0.0352   0.4394   1.0000
   3.250   0.3789   0.06838   0.05709  -0.0349   0.4367   1.0000
   3.500   0.4050   0.06877   0.05733  -0.0347   0.4348   1.0000
   3.750   0.3764   0.07388   0.06248  -0.0340   0.4245   1.0000
   4.000   0.3952   0.07497   0.06346  -0.0337   0.4215   1.0000
   4.250   0.4182   0.07571   0.06409  -0.0336   0.4193   1.0000
   4.750   0.4071   0.08270   0.07105  -0.0332   0.4090   1.0000
   5.000   0.4231   0.08418   0.07245  -0.0331   0.4061   1.0000
   5.250   0.4446   0.08516   0.07333  -0.0330   0.4040   1.0000
   5.500   0.4403   0.08859   0.07676  -0.0330   0.3992   1.0000
   5.750   0.4391   0.09184   0.08001  -0.0330   0.3952   1.0000
   6.000   0.4484   0.09415   0.08227  -0.0331   0.3925   1.0000
   6.250   0.4634   0.09590   0.08398  -0.0332   0.3903   1.0000
   6.500   0.4833   0.09719   0.08521  -0.0332   0.3884   1.0000
   6.750   0.4849   0.10020   0.08820  -0.0333   0.3849   1.0000
   7.000   0.4797   0.10382   0.09184  -0.0335   0.3808   1.0000
   7.250   0.4861   0.10647   0.09448  -0.0337   0.3783   1.0000
   7.500   0.4973   0.10866   0.09666  -0.0339   0.3761   1.0000
   7.750   0.5140   0.11036   0.09832  -0.0340   0.3741   1.0000
   8.000   0.5352   0.11166   0.09957  -0.0341   0.3723   1.0000
   8.250   0.5266   0.11542   0.10337  -0.0344   0.3684   1.0000
   8.500   0.5254   0.11863   0.10660  -0.0347   0.3656   1.0000
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