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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 100,000
Max Cl/Cd: 43.11 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe505-il-100000-n5.txt
Download as CSV file: xf-goe505-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1493   0.09609   0.09102  -0.0864   0.9375   0.0526
  -9.000  -0.1479   0.09230   0.08724  -0.0887   0.9333   0.0527
  -8.750  -0.1416   0.08834   0.08327  -0.0919   0.9303   0.0524
  -8.500  -0.1507   0.08569   0.08065  -0.0912   0.9232   0.0521
  -8.250  -0.1543   0.08218   0.07716  -0.0928   0.9178   0.0517
  -8.000  -0.1561   0.07786   0.07283  -0.0963   0.9139   0.0512
  -7.750  -0.1802   0.07586   0.07087  -0.0928   0.9038   0.0510
  -7.500  -0.1808   0.07063   0.06558  -0.0962   0.8994   0.0506
  -7.250  -0.2016   0.06762   0.06256  -0.0933   0.8898   0.0503
  -7.000  -0.2050   0.06123   0.05601  -0.0960   0.8852   0.0502
  -6.750  -0.2256   0.05631   0.05093  -0.0933   0.8760   0.0506
  -6.500  -0.2402   0.04622   0.04016  -0.0941   0.8708   0.0511
  -6.250  -0.2506   0.04235   0.03581  -0.0901   0.8632   0.0513
  -6.000  -0.2432   0.03888   0.03177  -0.0882   0.8586   0.0517
  -5.750  -0.2237   0.03612   0.02846  -0.0876   0.8558   0.0522
  -5.500  -0.2134   0.03459   0.02657  -0.0849   0.8503   0.0526
  -5.250  -0.1981   0.03326   0.02489  -0.0829   0.8450   0.0532
  -5.000  -0.1721   0.03187   0.02322  -0.0827   0.8420   0.0540
  -4.750  -0.1418   0.03090   0.02215  -0.0833   0.8398   0.0552
  -4.500  -0.1319   0.03064   0.02184  -0.0802   0.8323   0.0567
  -4.250  -0.1068   0.02995   0.02101  -0.0797   0.8281   0.0585
  -4.000  -0.0750   0.02902   0.01988  -0.0803   0.8253   0.0607
  -3.750  -0.0377   0.02795   0.01860  -0.0816   0.8231   0.0625
  -3.500  -0.0281   0.02766   0.01824  -0.0782   0.8127   0.0639
  -3.250   0.0130   0.02648   0.01701  -0.0800   0.8087   0.0671
  -3.000   0.0338   0.02590   0.01635  -0.0782   0.7992   0.0705
  -2.750   0.0704   0.02482   0.01521  -0.0791   0.7938   0.0771
  -2.500   0.1122   0.02378   0.01417  -0.0811   0.7909   0.0912
  -2.250   0.1202   0.02380   0.01420  -0.0774   0.7803   0.1030
  -2.000   0.1544   0.02320   0.01367  -0.0782   0.7765   0.1249
  -1.750   0.1945   0.02261   0.01306  -0.0801   0.7739   0.1479
  -1.500   0.2002   0.02288   0.01332  -0.0760   0.7622   0.1610
  -1.250   0.2373   0.02242   0.01286  -0.0772   0.7584   0.1829
  -1.000   0.2468   0.02264   0.01308  -0.0738   0.7473   0.1978
  -0.750   0.2813   0.02218   0.01261  -0.0746   0.7425   0.2186
  -0.500   0.2927   0.02228   0.01270  -0.0714   0.7308   0.2303
  -0.250   0.3287   0.02171   0.01210  -0.0724   0.7256   0.2468
   0.000   0.3403   0.02181   0.01222  -0.0693   0.7128   0.2570
   0.250   0.3591   0.02175   0.01217  -0.0675   0.7012   0.2685
   0.500   0.3881   0.02140   0.01180  -0.0674   0.6918   0.2834
   0.750   0.4138   0.02116   0.01155  -0.0667   0.6798   0.2986
   1.000   0.4378   0.02097   0.01137  -0.0657   0.6659   0.3155
   1.250   0.4647   0.02069   0.01108  -0.0653   0.6518   0.3353
   1.500   0.4940   0.02033   0.01070  -0.0652   0.6371   0.3587
   1.750   0.5237   0.01990   0.01027  -0.0651   0.6212   0.3867
   2.000   0.5536   0.01940   0.00978  -0.0651   0.6033   0.4311
   2.500   0.7581   0.01853   0.00953  -0.0947   0.5399   1.0000
   2.750   0.7755   0.01876   0.00952  -0.0926   0.5192   1.0000
   3.000   0.7910   0.01905   0.00960  -0.0902   0.5008   1.0000
   3.250   0.8065   0.01936   0.00972  -0.0879   0.4845   1.0000
   3.750   0.8384   0.02002   0.01007  -0.0836   0.4568   1.0000
   4.000   0.8553   0.02036   0.01028  -0.0817   0.4454   1.0000
   4.250   0.8736   0.02071   0.01047  -0.0801   0.4357   1.0000
   4.500   0.8917   0.02106   0.01073  -0.0784   0.4269   1.0000
   4.750   0.9117   0.02141   0.01097  -0.0771   0.4196   1.0000
   5.000   0.9300   0.02177   0.01128  -0.0756   0.4120   1.0000
   5.250   0.9503   0.02215   0.01154  -0.0744   0.4054   1.0000
   5.500   0.9688   0.02253   0.01190  -0.0729   0.3986   1.0000
   5.750   0.9875   0.02293   0.01222  -0.0715   0.3919   1.0000
   6.000   1.0063   0.02334   0.01256  -0.0701   0.3854   1.0000
   6.250   1.0223   0.02376   0.01298  -0.0683   0.3783   1.0000
   6.500   1.0419   0.02419   0.01330  -0.0671   0.3722   1.0000
   6.750   1.0576   0.02463   0.01377  -0.0653   0.3659   1.0000
   7.000   1.0755   0.02508   0.01421  -0.0638   0.3605   1.0000
   7.250   1.0967   0.02552   0.01458  -0.0630   0.3559   1.0000
   7.500   1.1144   0.02599   0.01511  -0.0616   0.3513   1.0000
   7.750   1.1323   0.02647   0.01564  -0.0602   0.3469   1.0000
   8.000   1.1515   0.02695   0.01614  -0.0591   0.3426   1.0000
   8.250   1.1744   0.02742   0.01655  -0.0586   0.3387   1.0000
   8.500   1.1889   0.02799   0.01723  -0.0568   0.3343   1.0000
   8.750   1.2048   0.02855   0.01786  -0.0553   0.3297   1.0000
   9.000   1.2225   0.02908   0.01843  -0.0540   0.3255   1.0000
   9.250   1.2444   0.02959   0.01889  -0.0534   0.3217   1.0000
   9.500   1.2542   0.03028   0.01976  -0.0511   0.3169   1.0000
   9.750   1.2641   0.03093   0.02048  -0.0488   0.3109   1.0000
  10.000   1.2786   0.03148   0.02097  -0.0472   0.3052   1.0000
  10.250   1.2804   0.03237   0.02205  -0.0440   0.2984   1.0000
  10.500   1.2860   0.03311   0.02281  -0.0414   0.2912   1.0000
  10.750   1.2923   0.03399   0.02379  -0.0390   0.2849   1.0000
  11.000   1.2972   0.03494   0.02484  -0.0366   0.2782   1.0000
  11.250   1.3040   0.03584   0.02575  -0.0345   0.2722   1.0000
  11.500   1.3100   0.03694   0.02706  -0.0325   0.2663   1.0000
  11.750   1.3148   0.03803   0.02821  -0.0304   0.2601   1.0000
  12.000   1.3187   0.03930   0.02960  -0.0284   0.2533   1.0000
  12.250   1.3194   0.04072   0.03109  -0.0262   0.2451   1.0000
  12.500   1.3225   0.04220   0.03271  -0.0244   0.2378   1.0000
  12.750   1.3233   0.04384   0.03442  -0.0226   0.2300   1.0000
  13.000   1.3255   0.04559   0.03631  -0.0211   0.2225   1.0000
  13.250   1.3255   0.04751   0.03830  -0.0195   0.2154   1.0000
  13.500   1.3227   0.04984   0.04073  -0.0181   0.2048   1.0000
  13.750   1.3196   0.05231   0.04328  -0.0168   0.1959   1.0000
  14.000   1.3130   0.05523   0.04622  -0.0157   0.1871   1.0000
  14.250   1.3074   0.05829   0.04937  -0.0149   0.1783   1.0000
  14.500   1.2971   0.06198   0.05311  -0.0142   0.1698   1.0000
  14.750   1.2836   0.06629   0.05747  -0.0139   0.1606   1.0000
  15.000   1.2717   0.07065   0.06194  -0.0140   0.1530   1.0000
  15.500   1.2417   0.08079   0.07233  -0.0150   0.1381   1.0000
  15.750   1.2253   0.08634   0.07801  -0.0160   0.1301   1.0000
  16.000   1.2102   0.09184   0.08366  -0.0171   0.1192   1.0000
  16.250   1.1866   0.09869   0.09051  -0.0188   0.0955   1.0000
  16.500   1.1669   0.10508   0.09692  -0.0205   0.0862   1.0000
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