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GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 615 AIRFOIL (goe615-il)
Reynolds number: 50,000
Max Cl/Cd: 30.49 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe615-il-50000-n5.txt
Download as CSV file: xf-goe615-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 615 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2550   0.13049   0.12367  -0.0385   1.0000   0.1300
 -10.250  -0.2728   0.13026   0.12358  -0.0378   1.0000   0.1307
 -10.000  -0.2918   0.12993   0.12338  -0.0367   1.0000   0.1311
  -9.750  -0.2642   0.12399   0.11745  -0.0335   1.0000   0.1341
  -9.500  -0.2642   0.12213   0.11566  -0.0312   1.0000   0.1374
  -9.250  -0.2719   0.12093   0.11455  -0.0293   1.0000   0.1409
  -9.000  -0.2820   0.11972   0.11341  -0.0327   0.9952   0.1459
  -8.750  -0.2800   0.11667   0.11041  -0.0389   0.9861   0.1474
  -8.500  -0.2454   0.11109   0.10477  -0.0395   0.9824   0.1502
  -8.250  -0.2274   0.10741   0.10108  -0.0423   0.9748   0.1529
  -8.000  -0.2141   0.10405   0.09771  -0.0457   0.9665   0.1562
  -7.500  -0.2304   0.09157   0.08517  -0.0628   0.9410   0.1010
  -7.250  -0.2112   0.08823   0.08179  -0.0634   0.9327   0.0973
  -6.750  -0.1972   0.07560   0.06893  -0.0784   0.9115   0.0862
  -6.500  -0.1880   0.07235   0.06565  -0.0795   0.9003   0.0853
  -6.250  -0.1667   0.06750   0.06065  -0.0846   0.8938   0.0842
  -6.000  -0.1607   0.06364   0.05664  -0.0864   0.8815   0.0841
  -5.750  -0.1419   0.05885   0.05156  -0.0906   0.8738   0.0844
  -5.500  -0.1290   0.05512   0.04755  -0.0922   0.8632   0.0844
  -5.250  -0.1065   0.05118   0.04322  -0.0948   0.8560   0.0841
  -5.000  -0.0899   0.04813   0.03981  -0.0953   0.8459   0.0839
  -4.750  -0.0579   0.04463   0.03579  -0.0981   0.8411   0.0841
  -4.500  -0.0452   0.04275   0.03352  -0.0967   0.8293   0.0852
  -4.250  -0.0118   0.04022   0.03036  -0.0985   0.8244   0.0872
  -4.000   0.0042   0.03902   0.02903  -0.0971   0.8134   0.0884
  -3.750   0.0374   0.03732   0.02706  -0.0982   0.8080   0.0897
  -3.500   0.0575   0.03632   0.02584  -0.0972   0.7983   0.0909
  -3.250   0.0885   0.03511   0.02438  -0.0977   0.7920   0.0933
  -3.000   0.1159   0.03422   0.02323  -0.0975   0.7850   0.0967
  -2.750   0.1402   0.03355   0.02225  -0.0968   0.7767   0.0997
  -2.500   0.1762   0.03242   0.02106  -0.0979   0.7722   0.1029
  -2.250   0.1932   0.03218   0.02076  -0.0962   0.7620   0.1057
  -2.000   0.2273   0.03150   0.01991  -0.0969   0.7567   0.1121
  -1.750   0.2518   0.03118   0.01951  -0.0963   0.7494   0.1180
  -1.500   0.2770   0.03090   0.01920  -0.0957   0.7420   0.1247
  -1.250   0.3131   0.03026   0.01853  -0.0968   0.7377   0.1378
  -1.000   0.3280   0.03043   0.01875  -0.0949   0.7280   0.1513
  -0.750   0.3595   0.02990   0.01842  -0.0954   0.7226   0.1905
  -0.500   0.3896   0.02923   0.01821  -0.0957   0.7175   0.3049
  -0.250   0.4031   0.02916   0.01866  -0.0936   0.7082   0.4233
   0.000   0.4706   0.02736   0.01813  -0.0993   0.7043   1.0000
   0.250   0.4872   0.02779   0.01831  -0.0974   0.6939   1.0000
   0.500   0.5216   0.02759   0.01779  -0.0977   0.6870   1.0000
   0.750   0.5378   0.02802   0.01803  -0.0957   0.6763   1.0000
   1.000   0.5723   0.02781   0.01756  -0.0961   0.6696   1.0000
   1.250   0.5867   0.02837   0.01797  -0.0940   0.6594   1.0000
   1.500   0.6193   0.02827   0.01767  -0.0942   0.6529   1.0000
   1.750   0.6344   0.02883   0.01812  -0.0922   0.6431   1.0000
   2.000   0.6658   0.02877   0.01789  -0.0922   0.6363   1.0000
   2.250   0.6818   0.02931   0.01834  -0.0903   0.6266   1.0000
   2.500   0.7130   0.02923   0.01813  -0.0903   0.6194   1.0000
   2.750   0.7287   0.02978   0.01860  -0.0884   0.6095   1.0000
   3.000   0.7611   0.02964   0.01834  -0.0885   0.6022   1.0000
   3.250   0.7756   0.03023   0.01888  -0.0864   0.5917   1.0000
   3.500   0.8109   0.02997   0.01850  -0.0868   0.5845   1.0000
   3.750   0.8227   0.03066   0.01917  -0.0844   0.5733   1.0000
   4.000   0.8621   0.03024   0.01862  -0.0853   0.5663   1.0000
   4.250   0.8704   0.03105   0.01945  -0.0825   0.5542   1.0000
   4.500   0.8982   0.03113   0.01944  -0.0820   0.5452   1.0000
   4.750   0.9189   0.03145   0.01974  -0.0807   0.5345   1.0000
   5.000   0.9345   0.03200   0.02028  -0.0788   0.5233   1.0000
   5.250   0.9679   0.03184   0.02003  -0.0790   0.5143   1.0000
   5.500   0.9743   0.03277   0.02101  -0.0760   0.5018   1.0000
   5.750   0.9967   0.03305   0.02124  -0.0749   0.4917   1.0000
   6.000   1.0140   0.03351   0.02168  -0.0732   0.4807   1.0000
   6.250   1.0193   0.03448   0.02269  -0.0702   0.4691   1.0000
   6.500   1.0498   0.03443   0.02258  -0.0701   0.4603   1.0000
   6.750   1.0488   0.03571   0.02392  -0.0664   0.4483   1.0000
   7.000   1.0584   0.03662   0.02485  -0.0642   0.4380   1.0000
   7.250   1.0805   0.03691   0.02513  -0.0632   0.4292   1.0000
   7.500   1.0808   0.03843   0.02671  -0.0603   0.4186   1.0000
   7.750   1.1101   0.03833   0.02654  -0.0600   0.4113   1.0000
   8.000   1.1066   0.04017   0.02848  -0.0570   0.4010   1.0000
   8.250   1.1294   0.04049   0.02879  -0.0562   0.3939   1.0000
   8.500   1.1322   0.04212   0.03050  -0.0541   0.3850   1.0000
   8.750   1.1594   0.04220   0.03053  -0.0536   0.3787   1.0000
   9.000   1.1556   0.04442   0.03286  -0.0513   0.3702   1.0000
   9.250   1.1887   0.04411   0.03251  -0.0511   0.3647   1.0000
   9.500   1.1776   0.04703   0.03558  -0.0487   0.3568   1.0000
   9.750   1.2012   0.04731   0.03585  -0.0479   0.3504   1.0000
  10.000   1.2030   0.04935   0.03797  -0.0463   0.3434   1.0000
  10.250   1.2081   0.05112   0.03982  -0.0449   0.3363   1.0000
  10.500   1.2386   0.05081   0.03948  -0.0445   0.3302   1.0000
  10.750   1.2085   0.05588   0.04477  -0.0424   0.3230   1.0000
  11.000   1.2404   0.05522   0.04408  -0.0417   0.3170   1.0000
  11.250   1.2199   0.05973   0.04876  -0.0404   0.3104   1.0000
  11.500   1.2065   0.06376   0.05291  -0.0395   0.3033   1.0000
  11.750   1.2607   0.06039   0.04944  -0.0386   0.2976   1.0000
  12.000   1.1318   0.07948   0.06893  -0.0407   0.2876   1.0000
  12.250   1.1904   0.07411   0.06356  -0.0383   0.2839   1.0000
  12.500   1.0543   0.09900   0.08865  -0.0455   0.2702   1.0000
  12.750   1.0992   0.09441   0.08411  -0.0427   0.2670   1.0000
  13.000   1.1634   0.08716   0.07690  -0.0391   0.2652   1.0000
  13.250   1.0562   0.10897   0.09883  -0.0467   0.2509   1.0000
  13.500   1.0984   0.10462   0.09457  -0.0439   0.2486   1.0000
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