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GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 513 AIRFOIL (goe513-il)
Reynolds number: 100,000
Max Cl/Cd: 44.5 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe513-il-100000.txt
Download as CSV file: xf-goe513-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 513 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2831   0.09759   0.09343  -0.0396   0.9649   0.1766
  -7.250  -0.3261   0.09526   0.09110  -0.0439   0.9527   0.1842
  -7.000  -0.3447   0.09130   0.08712  -0.0448   0.9404   0.1866
  -6.750  -0.3078   0.08733   0.08316  -0.0459   0.9350   0.1890
  -6.500  -0.4781   0.05724   0.05152  -0.0429   0.9156   0.1018
  -6.250  -0.4554   0.05362   0.04774  -0.0433   0.9079   0.0990
  -6.000  -0.4513   0.04973   0.04351  -0.0405   0.8970   0.0963
  -5.750  -0.4380   0.04472   0.03773  -0.0389   0.8901   0.0937
  -5.500  -0.4281   0.04228   0.03485  -0.0358   0.8779   0.0937
  -5.250  -0.3910   0.03960   0.03166  -0.0372   0.8727   0.0940
  -5.000  -0.3739   0.03787   0.02959  -0.0349   0.8596   0.0941
  -4.750  -0.3461   0.03624   0.02765  -0.0344   0.8489   0.0946
  -4.500  -0.3039   0.03448   0.02563  -0.0362   0.8418   0.0959
  -4.250  -0.2744   0.03330   0.02426  -0.0359   0.8301   0.0976
  -4.000  -0.2259   0.03181   0.02250  -0.0387   0.8243   0.1013
  -3.750  -0.1948   0.03056   0.02137  -0.0389   0.8123   0.1046
  -3.500  -0.1440   0.02903   0.01982  -0.0422   0.8072   0.1098
  -3.250  -0.1132   0.02803   0.01881  -0.0420   0.7957   0.1150
  -3.000  -0.0656   0.02653   0.01739  -0.0446   0.7906   0.1274
  -2.750  -0.0100   0.02483   0.01614  -0.0486   0.7879   0.1690
  -2.500   0.0035   0.02498   0.01644  -0.0447   0.7735   0.2405
  -2.250   0.0254   0.02516   0.01651  -0.0423   0.7634   0.2810
  -2.000   0.0626   0.02484   0.01603  -0.0430   0.7550   0.3086
  -1.750   0.1273   0.02395   0.01510  -0.0493   0.7511   0.3380
  -1.500   0.1485   0.02376   0.01488  -0.0476   0.7366   0.3559
  -1.250   0.1846   0.02332   0.01439  -0.0488   0.7257   0.3792
  -1.000   0.2347   0.02261   0.01356  -0.0527   0.7160   0.4012
  -0.750   0.2664   0.02225   0.01320  -0.0533   0.7028   0.4109
  -0.500   0.3212   0.02170   0.01244  -0.0582   0.6926   0.4206
  -0.250   0.3606   0.02133   0.01209  -0.0604   0.6793   0.4285
   0.000   0.3943   0.02117   0.01189  -0.0615   0.6662   0.4387
   0.250   0.4511   0.02070   0.01140  -0.0671   0.6532   0.4529
   0.500   0.4991   0.02030   0.01099  -0.0710   0.6406   0.4691
   0.750   0.5202   0.02019   0.01098  -0.0696   0.6282   0.4876
   1.000   0.7259   0.02037   0.01219  -0.1031   0.6059   0.9512
   1.250   0.8768   0.02048   0.01180  -0.1274   0.5857   1.0000
   1.500   0.8925   0.02078   0.01202  -0.1251   0.5745   1.0000
   1.750   0.9152   0.02105   0.01210  -0.1242   0.5648   1.0000
   2.000   0.9345   0.02134   0.01227  -0.1226   0.5541   1.0000
   2.250   0.9534   0.02170   0.01252  -0.1210   0.5440   1.0000
   2.500   0.9758   0.02203   0.01267  -0.1200   0.5339   1.0000
   2.750   0.9906   0.02246   0.01306  -0.1176   0.5237   1.0000
   3.000   1.0150   0.02281   0.01322  -0.1171   0.5139   1.0000
   3.250   1.0259   0.02329   0.01373  -0.1140   0.5041   1.0000
   3.500   1.0500   0.02367   0.01393  -0.1134   0.4948   1.0000
   3.750   1.0591   0.02417   0.01449  -0.1100   0.4852   1.0000
   4.000   1.0811   0.02454   0.01471  -0.1090   0.4761   1.0000
   4.250   1.0900   0.02505   0.01527  -0.1056   0.4668   1.0000
   4.500   1.1092   0.02539   0.01549  -0.1040   0.4578   1.0000
   4.750   1.1191   0.02589   0.01603  -0.1008   0.4489   1.0000
   5.000   1.1346   0.02624   0.01632  -0.0985   0.4404   1.0000
   5.250   1.1491   0.02672   0.01677  -0.0962   0.4325   1.0000
   5.500   1.1586   0.02718   0.01725  -0.0929   0.4244   1.0000
   5.750   1.1852   0.02752   0.01741  -0.0928   0.4177   1.0000
   6.000   1.1844   0.02819   0.01824  -0.0877   0.4100   1.0000
   6.250   1.2035   0.02852   0.01849  -0.0862   0.4034   1.0000
   6.500   1.2169   0.02910   0.01905  -0.0837   0.3970   1.0000
   6.750   1.2222   0.02970   0.01974  -0.0798   0.3904   1.0000
   7.000   1.2460   0.03000   0.01992  -0.0792   0.3847   1.0000
   7.250   1.2558   0.03074   0.02071  -0.0762   0.3795   1.0000
   7.500   1.2591   0.03154   0.02161  -0.0721   0.3741   1.0000
   7.750   1.2768   0.03203   0.02208  -0.0705   0.3693   1.0000
   8.000   1.3089   0.03251   0.02240  -0.0715   0.3649   1.0000
   8.250   1.2983   0.03362   0.02375  -0.0651   0.3604   1.0000
   8.500   1.3017   0.03445   0.02466  -0.0611   0.3559   1.0000
   8.750   1.3210   0.03495   0.02514  -0.0599   0.3517   1.0000
   9.000   1.3566   0.03548   0.02553  -0.0617   0.3478   1.0000
   9.250   1.3386   0.03686   0.02716  -0.0542   0.3445   1.0000
   9.500   1.3266   0.03805   0.02851  -0.0480   0.3412   1.0000
   9.750   1.3258   0.03906   0.02960  -0.0436   0.3380   1.0000
  10.000   1.3438   0.03972   0.03026  -0.0424   0.3346   1.0000
  10.250   1.3925   0.04028   0.03069  -0.0464   0.3309   1.0000
  10.500   1.3505   0.04204   0.03270  -0.0357   0.3286   1.0000
  10.750   1.3134   0.04433   0.03523  -0.0270   0.3259   1.0000
  11.000   1.2816   0.04702   0.03811  -0.0201   0.3232   1.0000
  11.250   1.2636   0.04947   0.04069  -0.0154   0.3204   1.0000
  11.500   1.2674   0.05107   0.04235  -0.0132   0.3179   1.0000
  11.750   1.3270   0.05021   0.04138  -0.0166   0.3152   1.0000
  12.000   0.6121   0.14373   0.13593  -0.0215   0.3508   1.0000
  12.250   0.6389   0.14651   0.13873  -0.0214   0.3492   1.0000
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