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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 50,000
Max Cl/Cd: 39.31 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802b-il-50000-n5.txt
Download as CSV file: xf-goe802b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2873   0.11124   0.10495  -0.0254   1.0000   0.0661
  -8.000  -0.2973   0.11006   0.10387  -0.0230   1.0000   0.0668
  -7.750  -0.3064   0.10878   0.10268  -0.0211   1.0000   0.0676
  -7.500  -0.3135   0.10733   0.10132  -0.0199   1.0000   0.0685
  -7.250  -0.3194   0.10585   0.09992  -0.0195   1.0000   0.0693
  -7.000  -0.2936   0.10236   0.09638  -0.0283   0.9913   0.0702
  -6.750  -0.2745   0.09797   0.09199  -0.0312   0.9848   0.0713
  -6.500  -0.2510   0.09413   0.08810  -0.0364   0.9778   0.0728
  -6.250  -0.2262   0.09051   0.08442  -0.0425   0.9695   0.0742
  -6.000  -0.1981   0.08705   0.08087  -0.0494   0.9613   0.0751
  -5.750  -0.1733   0.08331   0.07708  -0.0540   0.9533   0.0758
  -5.500  -0.1443   0.07954   0.07324  -0.0592   0.9471   0.0777
  -5.250  -0.1179   0.07660   0.07018  -0.0643   0.9372   0.0792
  -5.000  -0.0859   0.07286   0.06636  -0.0694   0.9310   0.0806
  -4.750  -0.0597   0.06994   0.06331  -0.0732   0.9219   0.0819
  -4.500  -0.0238   0.06689   0.06007  -0.0788   0.9141   0.0827
  -4.250   0.0145   0.06334   0.05638  -0.0842   0.9093   0.0836
  -4.000   0.0377   0.06100   0.05391  -0.0862   0.8982   0.0845
  -3.750   0.0801   0.05821   0.05085  -0.0917   0.8921   0.0852
  -3.500   0.1087   0.05562   0.04812  -0.0942   0.8835   0.0860
  -3.250   0.1458   0.05342   0.04565  -0.0978   0.8754   0.0869
  -3.000   0.1877   0.05068   0.04268  -0.1021   0.8705   0.0873
  -2.750   0.2114   0.04898   0.04081  -0.1028   0.8589   0.0877
  -2.500   0.2517   0.04684   0.03837  -0.1061   0.8528   0.0880
  -2.250   0.2800   0.04545   0.03673  -0.1070   0.8423   0.0883
  -2.000   0.3172   0.04382   0.03479  -0.1092   0.8348   0.0884
  -1.750   0.3485   0.04242   0.03315  -0.1103   0.8255   0.0885
  -1.500   0.3805   0.04074   0.03125  -0.1116   0.8164   0.0890
  -1.250   0.4152   0.03950   0.02971  -0.1129   0.8082   0.0896
  -1.000   0.4448   0.03864   0.02856  -0.1131   0.7973   0.0898
  -0.750   0.4788   0.03746   0.02712  -0.1141   0.7890   0.0899
  -0.500   0.5068   0.03653   0.02598  -0.1140   0.7776   0.0899
  -0.250   0.5382   0.03555   0.02478  -0.1144   0.7682   0.0900
   0.000   0.5674   0.03473   0.02376  -0.1144   0.7574   0.0900
   0.250   0.5958   0.03401   0.02285  -0.1142   0.7467   0.0900
   0.500   0.6264   0.03315   0.02178  -0.1144   0.7369   0.0910
   0.750   0.6527   0.03262   0.02108  -0.1139   0.7253   0.0927
   1.000   0.6845   0.03183   0.02008  -0.1141   0.7163   0.0948
   1.250   0.7088   0.03158   0.01967  -0.1134   0.7039   0.0962
   1.500   0.7410   0.03068   0.01860  -0.1135   0.6957   0.1001
   1.750   0.7651   0.03024   0.01795  -0.1127   0.6829   0.1086
   2.000   0.7989   0.02856   0.01612  -0.1130   0.6754   0.1232
   2.250   0.8205   0.02802   0.01568  -0.1121   0.6624   0.1306
   2.500   0.8493   0.02751   0.01514  -0.1120   0.6528   0.1360
   2.750   0.8749   0.02742   0.01502  -0.1116   0.6413   0.1391
   3.000   0.9015   0.02727   0.01495  -0.1114   0.6305   0.1502
   3.500   0.9485   0.02617   0.01524  -0.1097   0.6093   1.0000
   3.750   0.9766   0.02631   0.01520  -0.1093   0.5997   1.0000
   4.000   0.9985   0.02686   0.01569  -0.1085   0.5879   1.0000
   4.250   1.0275   0.02700   0.01569  -0.1084   0.5792   1.0000
   4.500   1.0478   0.02768   0.01636  -0.1074   0.5675   1.0000
   4.750   1.0772   0.02783   0.01640  -0.1074   0.5591   1.0000
   5.000   1.0960   0.02861   0.01723  -0.1063   0.5474   1.0000
   5.250   1.1253   0.02881   0.01733  -0.1063   0.5393   1.0000
   5.500   1.1430   0.02970   0.01829  -0.1051   0.5282   1.0000
   5.750   1.1714   0.02995   0.01850  -0.1050   0.5200   1.0000
   6.000   1.1883   0.03086   0.01951  -0.1038   0.5088   1.0000
   6.250   1.2173   0.03097   0.01953  -0.1036   0.4995   1.0000
   6.500   1.2315   0.03186   0.02053  -0.1018   0.4864   1.0000
   6.750   1.2531   0.03228   0.02097  -0.1008   0.4749   1.0000
   7.000   1.2738   0.03274   0.02144  -0.0997   0.4632   1.0000
   7.250   1.2900   0.03353   0.02233  -0.0982   0.4518   1.0000
   7.500   1.3141   0.03386   0.02265  -0.0975   0.4421   1.0000
   7.750   1.3265   0.03489   0.02385  -0.0957   0.4308   1.0000
   8.000   1.3520   0.03511   0.02403  -0.0951   0.4213   1.0000
   8.250   1.3605   0.03632   0.02545  -0.0928   0.4099   1.0000
   8.500   1.3815   0.03678   0.02593  -0.0918   0.4001   1.0000
   8.750   1.3916   0.03785   0.02716  -0.0897   0.3889   1.0000
   9.000   1.4074   0.03860   0.02801  -0.0881   0.3787   1.0000
   9.250   1.4198   0.03948   0.02900  -0.0862   0.3678   1.0000
   9.500   1.4281   0.04060   0.03024  -0.0840   0.3569   1.0000
   9.750   1.4435   0.04119   0.03085  -0.0822   0.3461   1.0000
  10.000   1.4424   0.04286   0.03270  -0.0791   0.3352   1.0000
  10.250   1.4611   0.04335   0.03319  -0.0778   0.3250   1.0000
  10.500   1.4546   0.04552   0.03561  -0.0747   0.3139   1.0000
  10.750   1.4638   0.04660   0.03670  -0.0727   0.3032   1.0000
  11.000   1.4615   0.04857   0.03882  -0.0703   0.2919   1.0000
  11.250   1.4601   0.05059   0.04093  -0.0681   0.2811   1.0000
  11.500   1.4641   0.05212   0.04248  -0.0663   0.2705   1.0000
  11.750   1.4547   0.05520   0.04575  -0.0645   0.2605   1.0000
  12.000   1.4626   0.05643   0.04695  -0.0630   0.2509   1.0000
  12.250   1.4477   0.06049   0.05124  -0.0617   0.2417   1.0000
  12.500   1.4558   0.06185   0.05261  -0.0605   0.2334   1.0000
  12.750   1.4409   0.06635   0.05734  -0.0598   0.2256   1.0000
  13.000   1.4425   0.06877   0.05983  -0.0590   0.2184   1.0000
  13.250   1.4393   0.07197   0.06313  -0.0584   0.2119   1.0000
  13.500   1.4249   0.07688   0.06825  -0.0585   0.2054   1.0000
  13.750   1.4381   0.07774   0.06908  -0.0574   0.1991   1.0000
  14.000   1.4180   0.08378   0.07534  -0.0582   0.1937   1.0000
  14.250   1.3966   0.09031   0.08208  -0.0595   0.1881   1.0000
  14.500   1.4124   0.09077   0.08254  -0.0583   0.1828   1.0000
  14.750   1.3982   0.09641   0.08832  -0.0594   0.1782   1.0000
  15.000   1.3226   0.11403   0.10622  -0.0669   0.1722   1.0000
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