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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 50,000
Max Cl/Cd: 23.44 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe316-il-50000.txt
Download as CSV file: xf-goe316-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3961   0.10356   0.09722  -0.0085   1.0000   0.1532
  -7.750  -0.3960   0.10042   0.09418  -0.0111   1.0000   0.1566
  -7.500  -0.3825   0.09640   0.09018  -0.0099   1.0000   0.1657
  -7.250  -0.3863   0.09422   0.08811  -0.0168   1.0000   0.1710
  -7.000  -0.3731   0.09023   0.08416  -0.0147   1.0000   0.1830
  -6.750  -0.3636   0.08648   0.08048  -0.0144   1.0000   0.1937
  -6.500  -0.3577   0.08327   0.07735  -0.0161   1.0000   0.2063
  -6.250  -0.3512   0.08018   0.07433  -0.0173   1.0000   0.2212
  -6.000  -0.3438   0.07713   0.07134  -0.0173   1.0000   0.2378
  -5.750  -0.3371   0.07428   0.06859  -0.0167   1.0000   0.2569
  -5.500  -0.3381   0.07233   0.06672  -0.0187   1.0000   0.2805
  -5.250  -0.3325   0.06929   0.06382  -0.0135   1.0000   0.3017
  -5.000  -0.3383   0.06758   0.06223  -0.0114   1.0000   0.3290
  -4.750   0.0163   0.04489   0.03866  -0.0126   1.0000   1.0000
  -4.500   0.0304   0.04277   0.03660  -0.0144   1.0000   1.0000
  -4.250   0.0447   0.04074   0.03464  -0.0162   1.0000   1.0000
  -4.000   0.0590   0.03879   0.03277  -0.0180   1.0000   1.0000
  -3.750   0.0731   0.03695   0.03103  -0.0199   1.0000   1.0000
  -3.500   0.0320   0.03834   0.03264  -0.0095   1.0000   0.9725
  -3.250  -0.0227   0.04001   0.03461   0.0021   1.0000   0.9293
  -3.000  -0.0742   0.04136   0.03622   0.0121   1.0000   0.9032
  -2.750  -0.1263   0.04260   0.03769   0.0224   1.0000   0.8942
  -2.500  -0.1731   0.04314   0.03842   0.0311   1.0000   0.8804
  -2.250  -0.2202   0.04337   0.03883   0.0395   1.0000   0.8674
  -2.000  -0.0095   0.03655   0.02883  -0.0585   0.9539   0.2762
  -1.750   0.0632   0.03479   0.02598  -0.0659   0.9373   0.2157
  -1.500   0.1230   0.03299   0.02369  -0.0711   0.9206   0.1986
  -1.250   0.1829   0.03153   0.02172  -0.0758   0.9037   0.1834
  -1.000   0.2355   0.03010   0.01997  -0.0791   0.8856   0.1748
  -0.750   0.2838   0.02923   0.01871  -0.0810   0.8670   0.1705
  -0.500   0.3257   0.02805   0.01744  -0.0819   0.8479   0.1748
  -0.250   0.3590   0.02745   0.01672  -0.0813   0.8250   0.1776
   0.000   0.3916   0.02685   0.01598  -0.0801   0.8043   0.1803
   0.250   0.4180   0.02661   0.01561  -0.0784   0.7815   0.1848
   0.500   0.4435   0.02626   0.01526  -0.0768   0.7599   0.1961
   1.000   0.4928   0.02547   0.01509  -0.0742   0.7190   0.3076
   1.250   0.5223   0.02436   0.01511  -0.0725   0.7002   1.0000
   1.500   0.5476   0.02493   0.01522  -0.0710   0.6833   1.0000
   1.750   0.5724   0.02559   0.01554  -0.0701   0.6682   1.0000
   2.000   0.5971   0.02635   0.01607  -0.0696   0.6546   1.0000
   2.250   0.6219   0.02707   0.01661  -0.0690   0.6428   1.0000
   2.500   0.6477   0.02763   0.01698  -0.0683   0.6328   1.0000
   2.750   0.6709   0.02875   0.01805  -0.0684   0.6212   1.0000
   3.000   0.6950   0.02978   0.01900  -0.0684   0.6123   1.0000
   3.250   0.7193   0.03082   0.02001  -0.0684   0.6045   1.0000
   3.500   0.7417   0.03224   0.02143  -0.0687   0.5970   1.0000
   3.750   0.7646   0.03348   0.02267  -0.0688   0.5898   1.0000
   4.000   0.7865   0.03494   0.02417  -0.0690   0.5832   1.0000
   4.250   0.8050   0.03697   0.02627  -0.0696   0.5765   1.0000
   4.500   0.8294   0.03812   0.02742  -0.0695   0.5722   1.0000
   4.750   0.8384   0.04155   0.03100  -0.0709   0.5659   1.0000
   5.000   0.8534   0.04396   0.03348  -0.0715   0.5603   1.0000
   5.250   0.8788   0.04504   0.03461  -0.0711   0.5565   1.0000
   5.500   0.8671   0.05094   0.04066  -0.0735   0.5515   1.0000
   5.750   0.8633   0.05544   0.04523  -0.0748   0.5470   1.0000
   6.000   0.8874   0.05675   0.04660  -0.0743   0.5421   1.0000
   6.250   0.8741   0.06204   0.05193  -0.0756   0.5381   1.0000
   6.500   0.8531   0.06731   0.05721  -0.0760   0.5357   1.0000
   6.750   0.8468   0.07129   0.06122  -0.0762   0.5325   1.0000
   7.000   0.8755   0.07251   0.06255  -0.0756   0.5239   1.0000
   7.250   0.8604   0.07734   0.06740  -0.0762   0.5224   1.0000
   7.500   0.8528   0.08169   0.07180  -0.0767   0.5218   1.0000
   7.750   0.8485   0.08594   0.07611  -0.0774   0.5220   1.0000
   8.000   0.8523   0.09034   0.08064  -0.0788   0.5264   1.0000
   8.250   0.7614   0.10233   0.09259  -0.0861   0.6293   1.0000
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