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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.85 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe483-il-1000000-n5.txt
Download as CSV file: xf-goe483-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3015   0.11200   0.11040  -0.0228   1.0000   0.0037
  -9.250  -0.2951   0.10904   0.10745  -0.0237   1.0000   0.0038
  -9.000  -0.2891   0.10618   0.10461  -0.0245   1.0000   0.0039
  -8.500  -0.2738   0.10021   0.09865  -0.0271   0.9839   0.0039
  -8.250  -0.2505   0.09528   0.09371  -0.0337   0.9721   0.0040
  -8.000  -0.2202   0.09027   0.08867  -0.0419   0.9594   0.0040
  -7.000  -0.1592   0.07660   0.07462  -0.0565   0.8532   0.0040
  -6.750  -0.1507   0.07458   0.07254  -0.0575   0.8376   0.0048
  -6.500  -0.1400   0.07198   0.06988  -0.0595   0.8239   0.0049
  -6.250  -0.1275   0.06920   0.06706  -0.0619   0.8127   0.0051
  -5.750  -0.0958   0.06301   0.06079  -0.0680   0.7954   0.0058
  -5.250  -0.0553   0.05481   0.05248  -0.0765   0.7800   0.0037
  -4.750  -0.0046   0.04710   0.04463  -0.0853   0.7662   0.0035
  -4.250   0.0884   0.01341   0.00936  -0.1106   0.7569   0.0032
  -4.000   0.1160   0.01156   0.00710  -0.1109   0.7501   0.0035
  -3.750   0.1434   0.01054   0.00577  -0.1109   0.7429   0.0037
  -3.500   0.1709   0.00987   0.00487  -0.1108   0.7345   0.0040
  -3.250   0.1983   0.00906   0.00381  -0.1107   0.7251   0.0043
  -3.000   0.2255   0.00870   0.00334  -0.1105   0.7140   0.0049
  -2.750   0.2528   0.00844   0.00297  -0.1104   0.7024   0.0055
  -2.500   0.2804   0.00809   0.00248  -0.1102   0.6911   0.0062
  -2.250   0.3077   0.00782   0.00207  -0.1099   0.6782   0.0069
  -2.000   0.3350   0.00755   0.00169  -0.1097   0.6637   0.0088
  -1.750   0.3620   0.00747   0.00150  -0.1094   0.6461   0.0109
  -1.500   0.3890   0.00734   0.00128  -0.1092   0.6255   0.0181
  -1.250   0.4156   0.00732   0.00117  -0.1089   0.6001   0.0284
  -1.000   0.4423   0.00737   0.00110  -0.1086   0.5758   0.0328
  -0.750   0.4690   0.00738   0.00102  -0.1083   0.5564   0.0392
  -0.500   0.4959   0.00738   0.00097  -0.1081   0.5403   0.0485
  -0.250   0.5229   0.00738   0.00094  -0.1079   0.5277   0.0630
   0.000   0.5499   0.00739   0.00093  -0.1078   0.5163   0.0828
   0.250   0.5771   0.00741   0.00093  -0.1076   0.5065   0.0935
   0.500   0.6043   0.00745   0.00093  -0.1075   0.4976   0.1002
   0.750   0.6315   0.00748   0.00094  -0.1073   0.4884   0.1072
   1.000   0.6587   0.00751   0.00096  -0.1072   0.4799   0.1149
   1.250   0.6857   0.00756   0.00099  -0.1070   0.4713   0.1267
   1.500   0.7129   0.00759   0.00104  -0.1069   0.4620   0.1419
   1.750   0.7399   0.00764   0.00111  -0.1068   0.4521   0.1644
   2.000   0.7667   0.00771   0.00119  -0.1066   0.4395   0.1873
   2.250   0.7935   0.00781   0.00126  -0.1064   0.4254   0.1995
   2.500   0.8202   0.00792   0.00135  -0.1063   0.4120   0.2075
   2.750   0.8469   0.00803   0.00143  -0.1061   0.3998   0.2150
   3.000   0.8736   0.00813   0.00152  -0.1059   0.3888   0.2222
   3.250   0.9002   0.00825   0.00164  -0.1057   0.3766   0.2303
   3.500   0.9266   0.00838   0.00177  -0.1055   0.3641   0.2403
   3.750   0.9530   0.00851   0.00190  -0.1053   0.3532   0.2538
   4.000   0.9792   0.00865   0.00205  -0.1051   0.3408   0.2718
   4.250   1.0041   0.00893   0.00228  -0.1048   0.3113   0.2976
   4.750   1.0516   0.00863   0.00292  -0.1040   0.2357   1.0000
   5.250   1.0858   0.01135   0.00450  -0.1011   0.0221   1.0000
   5.500   1.1101   0.01174   0.00487  -0.1006   0.0101   1.0000
   5.750   1.1349   0.01206   0.00522  -0.1001   0.0073   1.0000
   6.000   1.1590   0.01247   0.00565  -0.0996   0.0055   1.0000
   6.250   1.1833   0.01283   0.00605  -0.0991   0.0047   1.0000
   6.500   1.2070   0.01327   0.00653  -0.0985   0.0039   1.0000
   6.750   1.2302   0.01374   0.00705  -0.0978   0.0033   1.0000
   7.000   1.2532   0.01422   0.00758  -0.0971   0.0029   1.0000
   7.250   1.2757   0.01473   0.00814  -0.0963   0.0026   1.0000
   7.500   1.2975   0.01529   0.00875  -0.0955   0.0023   1.0000
   7.750   1.3163   0.01619   0.00975  -0.0941   0.0021   1.0000
   8.000   1.3363   0.01690   0.01059  -0.0930   0.0019   1.0000
   8.250   1.3543   0.01779   0.01158  -0.0915   0.0018   1.0000
   8.500   1.3705   0.01879   0.01270  -0.0898   0.0017   1.0000
   8.750   1.3847   0.01992   0.01394  -0.0879   0.0016   1.0000
   9.000   1.4002   0.02083   0.01494  -0.0861   0.0015   1.0000
   9.250   1.4123   0.02198   0.01620  -0.0839   0.0014   1.0000
   9.500   1.4289   0.02263   0.01690  -0.0825   0.0013   1.0000
   9.750   1.4388   0.02363   0.01799  -0.0800   0.0012   1.0000
  10.000   1.4478   0.02452   0.01895  -0.0774   0.0011   1.0000
  10.250   1.4498   0.02598   0.02054  -0.0740   0.0011   1.0000
  10.500   1.4447   0.02825   0.02299  -0.0700   0.0011   1.0000
  10.750   1.4462   0.03017   0.02506  -0.0672   0.0010   1.0000
  11.000   1.4480   0.03222   0.02726  -0.0648   0.0010   1.0000
  11.250   1.4507   0.03430   0.02951  -0.0626   0.0010   1.0000
  11.500   1.4500   0.03706   0.03247  -0.0604   0.0010   1.0000
  11.750   1.4461   0.04050   0.03613  -0.0582   0.0009   1.0000
  12.000   1.4346   0.04705   0.04311  -0.0551   0.0008   1.0000
  12.250   1.4217   0.05247   0.04882  -0.0533   0.0007   1.0000
  12.500   1.4067   0.05755   0.05415  -0.0522   0.0007   1.0000
  12.750   1.3906   0.06274   0.05956  -0.0520   0.0007   1.0000
  13.000   1.3733   0.06835   0.06538  -0.0525   0.0007   1.0000
  13.250   1.3556   0.07433   0.07154  -0.0538   0.0007   1.0000
  13.500   1.3371   0.08079   0.07818  -0.0560   0.0007   1.0000
  13.750   1.3192   0.08758   0.08514  -0.0589   0.0007   1.0000
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