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GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 360 AIRFOIL (goe360-il)
Reynolds number: 200,000
Max Cl/Cd: 73.36 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe360-il-200000.txt
Download as CSV file: xf-goe360-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 360 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2400   0.09963   0.09642  -0.0321   1.0000   0.0297
  -8.250  -0.2461   0.09820   0.09507  -0.0307   1.0000   0.0303
  -8.000  -0.2639   0.09798   0.09494  -0.0266   1.0000   0.0305
  -7.750  -0.2468   0.09483   0.09179  -0.0337   0.9931   0.0319
  -7.500  -0.2112   0.09087   0.08778  -0.0535   0.9796   0.0324
  -7.250  -0.1863   0.08507   0.08196  -0.0590   0.9741   0.0327
  -7.000  -0.1666   0.08019   0.07710  -0.0580   0.9710   0.0333
  -6.750  -0.1437   0.07621   0.07310  -0.0616   0.9619   0.0341
  -6.500  -0.1175   0.07229   0.06914  -0.0671   0.9523   0.0352
  -6.250  -0.0917   0.06860   0.06538  -0.0727   0.9412   0.0369
  -6.000  -0.0535   0.06560   0.06217  -0.0841   0.9258   0.0393
  -5.750  -0.0216   0.06294   0.05921  -0.0910   0.9110   0.0397
  -5.500  -0.0170   0.05830   0.05466  -0.0887   0.8980   0.0402
  -5.250  -0.0061   0.05541   0.05176  -0.0873   0.8846   0.0409
  -5.000   0.0094   0.05282   0.04912  -0.0873   0.8710   0.0418
  -4.750   0.0291   0.05028   0.04647  -0.0882   0.8577   0.0432
  -4.500   0.0532   0.04776   0.04379  -0.0899   0.8448   0.0457
  -4.250   0.1008   0.04732   0.04264  -0.0948   0.8323   0.0487
  -4.000   0.1137   0.04218   0.03762  -0.0949   0.8199   0.0496
  -3.750   0.1322   0.03958   0.03500  -0.0949   0.8067   0.0507
  -3.500   0.1548   0.03745   0.03275  -0.0953   0.7942   0.0524
  -3.250   0.1810   0.03547   0.03058  -0.0959   0.7823   0.0552
  -3.000   0.2166   0.03406   0.02859  -0.0970   0.7714   0.0603
  -2.750   0.2373   0.03139   0.02596  -0.0972   0.7590   0.0620
  -2.500   0.2620   0.02971   0.02414  -0.0975   0.7468   0.0648
  -2.250   0.2977   0.03107   0.02483  -0.0971   0.7349   0.0720
  -2.000   0.3187   0.02673   0.02055  -0.0979   0.7247   0.0746
  -1.750   0.3439   0.02529   0.01902  -0.0980   0.7130   0.0787
  -1.500   0.3731   0.02429   0.01766  -0.0981   0.7015   0.0881
  -1.250   0.3986   0.02300   0.01629  -0.0982   0.6907   0.0942
  -1.000   0.4254   0.02196   0.01501  -0.0982   0.6804   0.1071
  -0.750   0.4519   0.02104   0.01395  -0.0983   0.6686   0.1234
  -0.500   0.4781   0.02018   0.01292  -0.0984   0.6574   0.1492
   0.000   0.5292   0.01833   0.01090  -0.0985   0.6360   0.2124
   0.250   0.5563   0.01767   0.01011  -0.0983   0.6246   0.2400
   0.500   0.5844   0.01685   0.00919  -0.0981   0.6139   0.2480
   0.750   0.6242   0.01723   0.00861  -0.0959   0.6039   0.1011
   1.000   0.6524   0.01658   0.00782  -0.0953   0.5925   0.0868
   1.250   0.6797   0.01585   0.00705  -0.0949   0.5818   0.0797
   1.500   0.7072   0.01559   0.00658  -0.0944   0.5714   0.0737
   1.750   0.7342   0.01549   0.00644  -0.0940   0.5591   0.0720
   2.000   0.7606   0.01509   0.00604  -0.0936   0.5476   0.0716
   2.250   0.7871   0.01487   0.00578  -0.0933   0.5371   0.0719
   2.500   0.8133   0.01453   0.00548  -0.0930   0.5263   0.0763
   2.750   0.8398   0.01445   0.00540  -0.0928   0.5148   0.0798
   3.000   0.8664   0.01446   0.00532  -0.0925   0.5042   0.0834
   3.250   0.8930   0.01451   0.00525  -0.0923   0.4946   0.0912
   3.500   0.9179   0.01292   0.00541  -0.0917   0.4844   1.0000
   3.750   0.9443   0.01319   0.00547  -0.0914   0.4757   1.0000
   4.000   0.9705   0.01345   0.00560  -0.0911   0.4667   1.0000
   4.250   0.9966   0.01374   0.00581  -0.0909   0.4580   1.0000
   4.500   1.0227   0.01405   0.00600  -0.0907   0.4502   1.0000
   4.750   1.0487   0.01435   0.00630  -0.0905   0.4423   1.0000
   5.000   1.0749   0.01468   0.00655  -0.0903   0.4357   1.0000
   5.250   1.1009   0.01503   0.00690  -0.0902   0.4289   1.0000
   5.500   1.1268   0.01536   0.00722  -0.0900   0.4223   1.0000
   5.750   1.1528   0.01576   0.00757  -0.0899   0.4165   1.0000
   6.000   1.1784   0.01609   0.00796  -0.0896   0.4102   1.0000
   6.250   1.2045   0.01649   0.00832  -0.0895   0.4051   1.0000
   6.500   1.2302   0.01692   0.00881  -0.0894   0.4000   1.0000
   6.750   1.2556   0.01729   0.00926  -0.0892   0.3946   1.0000
   7.000   1.2816   0.01771   0.00965  -0.0891   0.3898   1.0000
   7.250   1.3063   0.01812   0.01017  -0.0888   0.3840   1.0000
   7.500   1.3303   0.01839   0.01048  -0.0883   0.3765   1.0000
   7.750   1.3537   0.01871   0.01084  -0.0878   0.3685   1.0000
   8.000   1.3770   0.01896   0.01114  -0.0873   0.3607   1.0000
   8.250   1.3995   0.01927   0.01155  -0.0866   0.3526   1.0000
   8.500   1.4216   0.01950   0.01176  -0.0859   0.3434   1.0000
   8.750   1.4417   0.01971   0.01214  -0.0848   0.3333   1.0000
   9.000   1.4614   0.01996   0.01246  -0.0837   0.3225   1.0000
   9.250   1.4801   0.02022   0.01279  -0.0825   0.3108   1.0000
   9.500   1.4959   0.02045   0.01315  -0.0808   0.2935   1.0000
   9.750   1.5090   0.02086   0.01358  -0.0788   0.2697   1.0000
  10.000   1.5143   0.02180   0.01436  -0.0759   0.2181   1.0000
  10.250   1.4948   0.02441   0.01634  -0.0702   0.1329   1.0000
  10.500   1.4712   0.02792   0.01941  -0.0654   0.0739   1.0000
  10.750   1.4584   0.03095   0.02229  -0.0623   0.0478   1.0000
  11.000   1.4530   0.03361   0.02496  -0.0602   0.0409   1.0000
  11.250   1.4516   0.03608   0.02759  -0.0587   0.0379   1.0000
  11.500   1.4474   0.03899   0.03064  -0.0575   0.0359   1.0000
  11.750   1.4401   0.04242   0.03421  -0.0567   0.0345   1.0000
  12.000   1.4299   0.04642   0.03837  -0.0562   0.0335   1.0000
  12.250   1.4218   0.05036   0.04247  -0.0561   0.0329   1.0000
  12.500   1.4142   0.05435   0.04662  -0.0561   0.0323   1.0000
  12.750   1.4054   0.05855   0.05097  -0.0563   0.0318   1.0000
  13.000   1.3962   0.06289   0.05544  -0.0566   0.0312   1.0000
  13.250   1.3870   0.06732   0.05999  -0.0569   0.0306   1.0000
  13.500   1.3785   0.07172   0.06450  -0.0574   0.0299   1.0000
  13.750   1.3708   0.07603   0.06890  -0.0578   0.0292   1.0000
  14.000   1.3638   0.08022   0.07315  -0.0582   0.0286   1.0000
  14.250   1.3585   0.08410   0.07710  -0.0584   0.0280   1.0000
  14.500   1.3558   0.08736   0.08037  -0.0581   0.0273   1.0000
  14.750   1.3595   0.08904   0.08202  -0.0564   0.0266   1.0000
  15.000   1.3673   0.09055   0.08357  -0.0550   0.0262   1.0000
  15.250   1.3753   0.09229   0.08539  -0.0540   0.0259   1.0000
  15.500   1.3848   0.09378   0.08697  -0.0528   0.0255   1.0000
  15.750   1.3928   0.09560   0.08891  -0.0519   0.0250   1.0000
  16.000   1.3995   0.09771   0.09113  -0.0512   0.0245   1.0000
  16.250   1.4049   0.10008   0.09362  -0.0508   0.0239   1.0000
  16.500   1.4103   0.10246   0.09613  -0.0504   0.0234   1.0000
  16.750   1.4161   0.10485   0.09866  -0.0498   0.0231   1.0000
  17.000   1.4197   0.10770   0.10167  -0.0496   0.0230   1.0000
  17.250   1.4201   0.11117   0.10535  -0.0499   0.0230   1.0000
  17.500   1.4170   0.11531   0.10971  -0.0508   0.0231   1.0000
  17.750   1.4107   0.12015   0.11479  -0.0523   0.0233   1.0000
  18.000   1.4015   0.12561   0.12049  -0.0545   0.0236   1.0000
  18.250   1.3904   0.13162   0.12674  -0.0572   0.0239   1.0000
  18.500   1.3777   0.13807   0.13342  -0.0605   0.0242   1.0000
  18.750   1.3640   0.14493   0.14050  -0.0644   0.0246   1.0000
  19.000   1.3498   0.15211   0.14789  -0.0686   0.0249   1.0000
  19.250   1.3351   0.15966   0.15561  -0.0733   0.0253   1.0000
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