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GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 432 AIRFOIL (goe432-il)
Reynolds number: 100,000
Max Cl/Cd: 53.34 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe432-il-100000.txt
Download as CSV file: xf-goe432-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 432 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3628   0.09900   0.09419  -0.0238   1.0000   0.0700
  -7.750  -0.3777   0.09835   0.09367  -0.0251   1.0000   0.0707
  -7.500  -0.3820   0.09659   0.09197  -0.0293   1.0000   0.0711
  -7.250  -0.3760   0.09103   0.08648  -0.0250   1.0000   0.0725
  -7.000  -0.3651   0.08763   0.08309  -0.0207   1.0000   0.0758
  -6.750  -0.3639   0.08508   0.08059  -0.0204   1.0000   0.0786
  -6.500  -0.3636   0.08255   0.07811  -0.0216   1.0000   0.0815
  -6.250  -0.3598   0.08062   0.07615  -0.0316   1.0000   0.0850
  -6.000  -0.3553   0.07631   0.07186  -0.0328   1.0000   0.0861
  -5.750  -0.3525   0.07297   0.06862  -0.0274   1.0000   0.0879
  -5.500  -0.3465   0.07031   0.06600  -0.0255   1.0000   0.0909
  -5.250  -0.3367   0.06741   0.06308  -0.0271   1.0000   0.0960
  -5.000  -0.3114   0.05256   0.04864  -0.0258   1.0000   0.1020
  -4.750  -0.3071   0.04991   0.04604  -0.0230   1.0000   0.1054
  -4.250  -0.2856   0.05445   0.04994  -0.0329   1.0000   0.1190
  -4.000  -0.2671   0.05149   0.04683  -0.0350   1.0000   0.1323
  -3.750  -0.2491   0.04895   0.04416  -0.0362   1.0000   0.1465
  -3.500  -0.2381   0.04668   0.04198  -0.0340   1.0000   0.1534
  -3.250  -0.2203   0.04428   0.03950  -0.0344   1.0000   0.1685
  -3.000  -0.1998   0.04203   0.03709  -0.0355   1.0000   0.1918
  -2.750  -0.1856   0.04010   0.03520  -0.0341   1.0000   0.2103
  -2.250  -0.0897   0.02809   0.02106  -0.0425   1.0000   0.1033
  -2.000  -0.0552   0.02636   0.01858  -0.0431   0.9978   0.0995
  -1.750  -0.0041   0.02426   0.01592  -0.0471   0.9889   0.1001
  -1.500   0.0438   0.02235   0.01390  -0.0512   0.9796   0.1075
  -1.250   0.0962   0.02133   0.01248  -0.0554   0.9697   0.1155
  -1.000   0.1437   0.02010   0.01128  -0.0589   0.9579   0.1239
  -0.750   0.1901   0.01916   0.01039  -0.0622   0.9449   0.1376
  -0.500   0.2365   0.01823   0.00956  -0.0653   0.9312   0.1543
  -0.250   0.2830   0.01722   0.00888  -0.0683   0.9170   0.2075
   0.000   0.3534   0.01462   0.00812  -0.0756   0.9096   1.0000
   0.250   0.4020   0.01417   0.00746  -0.0787   0.8909   1.0000
   0.500   0.4498   0.01365   0.00677  -0.0814   0.8716   1.0000
   0.750   0.4913   0.01319   0.00616  -0.0828   0.8456   1.0000
   1.000   0.5318   0.01284   0.00564  -0.0841   0.8164   1.0000
   1.250   0.5685   0.01270   0.00529  -0.0847   0.7841   1.0000
   1.500   0.6004   0.01276   0.00512  -0.0847   0.7516   1.0000
   1.750   0.6277   0.01295   0.00510  -0.0839   0.7194   1.0000
   2.000   0.6541   0.01321   0.00515  -0.0830   0.6910   1.0000
   2.250   0.6793   0.01350   0.00527  -0.0821   0.6649   1.0000
   2.500   0.7043   0.01382   0.00543  -0.0812   0.6416   1.0000
   2.750   0.7292   0.01415   0.00560  -0.0802   0.6198   1.0000
   3.000   0.7535   0.01450   0.00581  -0.0792   0.5984   1.0000
   3.250   0.7779   0.01487   0.00606  -0.0783   0.5789   1.0000
   3.500   0.8027   0.01527   0.00635  -0.0774   0.5615   1.0000
   3.750   0.8275   0.01569   0.00670  -0.0766   0.5450   1.0000
   4.000   0.8521   0.01613   0.00706  -0.0758   0.5289   1.0000
   4.250   0.8763   0.01657   0.00745  -0.0749   0.5124   1.0000
   4.500   0.8998   0.01699   0.00787  -0.0739   0.4951   1.0000
   4.750   0.9229   0.01740   0.00831  -0.0729   0.4767   1.0000
   5.000   0.9457   0.01779   0.00868  -0.0717   0.4569   1.0000
   5.250   0.9678   0.01817   0.00902  -0.0704   0.4352   1.0000
   5.500   0.9890   0.01854   0.00935  -0.0689   0.4107   1.0000
   5.750   1.0095   0.01897   0.00976  -0.0673   0.3840   1.0000
   6.000   1.0300   0.01947   0.01017  -0.0659   0.3586   1.0000
   6.250   1.0513   0.02004   0.01063  -0.0646   0.3370   1.0000
   6.500   1.0739   0.02073   0.01123  -0.0636   0.3202   1.0000
   6.750   1.0967   0.02144   0.01195  -0.0627   0.3057   1.0000
   7.000   1.1193   0.02213   0.01270  -0.0617   0.2925   1.0000
   7.250   1.1417   0.02283   0.01350  -0.0607   0.2804   1.0000
   7.500   1.1641   0.02358   0.01432  -0.0598   0.2694   1.0000
   7.750   1.1873   0.02439   0.01517  -0.0590   0.2598   1.0000
   8.000   1.2100   0.02520   0.01608  -0.0581   0.2499   1.0000
   8.250   1.2316   0.02616   0.01721  -0.0571   0.2403   1.0000
   8.500   1.2540   0.02713   0.01823  -0.0563   0.2307   1.0000
   8.750   1.2762   0.02801   0.01908  -0.0554   0.2196   1.0000
   9.000   1.2926   0.02860   0.01973  -0.0538   0.2053   1.0000
   9.250   1.3064   0.02918   0.02040  -0.0518   0.1901   1.0000
   9.500   1.3218   0.03001   0.02127  -0.0502   0.1765   1.0000
   9.750   1.3374   0.03101   0.02229  -0.0487   0.1633   1.0000
  10.000   1.3473   0.03176   0.02327  -0.0462   0.1495   1.0000
  10.250   1.3512   0.03233   0.02411  -0.0429   0.1336   1.0000
  10.500   1.3483   0.03265   0.02476  -0.0385   0.1120   1.0000
  10.750   1.3426   0.03380   0.02585  -0.0341   0.0912   1.0000
  11.000   1.3375   0.03593   0.02789  -0.0301   0.0777   1.0000
  11.250   1.3354   0.03828   0.03022  -0.0270   0.0695   1.0000
  11.500   1.3345   0.04039   0.03238  -0.0244   0.0630   1.0000
  11.750   1.3349   0.04286   0.03497  -0.0221   0.0583   1.0000
  12.000   1.3372   0.04525   0.03752  -0.0201   0.0548   1.0000
  12.250   1.3402   0.04774   0.04004  -0.0185   0.0520   1.0000
  12.500   1.3444   0.05089   0.04331  -0.0171   0.0498   1.0000
  12.750   1.3424   0.05393   0.04666  -0.0157   0.0481   1.0000
  13.000   1.3371   0.05719   0.05017  -0.0147   0.0465   1.0000
  13.250   1.3316   0.06054   0.05373  -0.0143   0.0449   1.0000
  13.500   1.3270   0.06416   0.05751  -0.0140   0.0438   1.0000
  13.750   1.3222   0.06807   0.06157  -0.0141   0.0428   1.0000
  14.000   1.3151   0.07253   0.06620  -0.0145   0.0422   1.0000
  14.250   1.3027   0.07770   0.07159  -0.0157   0.0420   1.0000
  14.500   1.2857   0.08354   0.07769  -0.0179   0.0419   1.0000
  14.750   1.2626   0.09046   0.08490  -0.0216   0.0422   1.0000
  15.000   1.2247   0.10061   0.09543  -0.0284   0.0433   1.0000
  15.250   1.1554   0.11939   0.11463  -0.0416   0.0473   1.0000
  15.500   1.1184   0.13298   0.12828  -0.0501   0.0496   1.0000
  15.750   1.0923   0.14488   0.14021  -0.0570   0.0507   1.0000
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