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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 50,000
Max Cl/Cd: 20.52 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe05k-il-50000.txt
Download as CSV file: xf-goe05k-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 5K 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5621   0.10889   0.10220  -0.0093   1.0000   0.1390
  -8.000  -0.5477   0.10313   0.09640  -0.0073   1.0000   0.1507
  -7.750  -0.5586   0.10200   0.09541  -0.0103   1.0000   0.1537
  -7.500  -0.5483   0.09712   0.09055  -0.0081   1.0000   0.1658
  -7.250  -0.5454   0.09347   0.08697  -0.0084   1.0000   0.1748
  -7.000  -0.5497   0.09175   0.08534  -0.0129   1.0000   0.1833
  -6.750  -0.5449   0.08800   0.08165  -0.0125   1.0000   0.1980
  -6.500  -0.5415   0.08479   0.07848  -0.0134   1.0000   0.2133
  -6.250  -0.5335   0.08027   0.07403  -0.0100   1.0000   0.2324
  -6.000  -0.5310   0.07754   0.07134  -0.0107   1.0000   0.2573
  -5.750  -0.5252   0.07392   0.06778  -0.0076   1.0000   0.2859
  -5.500  -0.5222   0.07068   0.06460  -0.0054   1.0000   0.3197
  -5.250  -0.5184   0.06746   0.06147  -0.0001   1.0000   0.3650
  -5.000  -0.2326   0.04542   0.03841   0.0007   1.0000   0.9683
  -4.750  -0.2491   0.04484   0.03803   0.0060   1.0000   0.9441
  -4.500  -0.2852   0.04541   0.03878   0.0146   1.0000   0.9013
  -4.250  -0.3236   0.04582   0.03941   0.0224   1.0000   0.8565
  -4.000  -0.3602   0.04570   0.03953   0.0286   1.0000   0.8129
  -3.750  -0.3947   0.04528   0.03934   0.0342   1.0000   0.7795
  -3.500  -0.4314   0.04423   0.03856   0.0396   1.0000   0.7429
  -3.250  -0.3004   0.03497   0.02633  -0.0344   1.0000   0.1804
  -3.000  -0.2647   0.03200   0.02248  -0.0345   1.0000   0.1367
  -2.750  -0.2345   0.02919   0.01906  -0.0336   1.0000   0.1155
  -2.500  -0.2056   0.02690   0.01623  -0.0325   1.0000   0.1025
  -2.250  -0.1766   0.02508   0.01379  -0.0311   1.0000   0.0946
  -2.000  -0.1486   0.02321   0.01153  -0.0299   1.0000   0.0956
  -1.750  -0.1203   0.02123   0.00932  -0.0287   1.0000   0.0992
  -1.500  -0.0917   0.01962   0.00753  -0.0278   1.0000   0.1145
  -1.250  -0.0651   0.01808   0.00599  -0.0270   1.0000   0.1540
  -1.000  -0.0213   0.01448   0.00427  -0.0282   1.0000   1.0000
  -0.750   0.0018   0.01451   0.00364  -0.0271   1.0000   1.0000
  -0.500   0.0246   0.01456   0.00328  -0.0262   1.0000   1.0000
  -0.250   0.0472   0.01463   0.00303  -0.0254   1.0000   1.0000
   0.000   0.0698   0.01472   0.00288  -0.0245   1.0000   1.0000
   0.250   0.0923   0.01482   0.00278  -0.0237   1.0000   1.0000
   0.500   0.1147   0.01494   0.00279  -0.0230   1.0000   1.0000
   0.750   0.1371   0.01508   0.00285  -0.0222   1.0000   1.0000
   1.000   0.1592   0.01523   0.00300  -0.0214   1.0000   1.0000
   1.250   0.1814   0.01540   0.00322  -0.0207   1.0000   1.0000
   1.500   0.2033   0.01559   0.00350  -0.0199   1.0000   1.0000
   1.750   0.2252   0.01580   0.00385  -0.0191   1.0000   1.0000
   2.000   0.2469   0.01604   0.00429  -0.0183   1.0000   1.0000
   2.250   0.2685   0.01630   0.00489  -0.0175   1.0000   1.0000
   2.500   0.2900   0.01658   0.00549  -0.0168   1.0000   1.0000
   2.750   0.3114   0.01691   0.00623  -0.0160   1.0000   1.0000
   3.000   0.3325   0.01727   0.00721  -0.0150   1.0000   1.0000
   3.250   0.3540   0.01766   0.00840  -0.0140   1.0000   1.0000
   3.500   0.5369   0.02617   0.01402  -0.0332   0.0821   1.0000
   3.750   0.5702   0.02878   0.01699  -0.0324   0.0809   1.0000
   4.000   0.6008   0.03231   0.02075  -0.0317   0.0844   1.0000
   4.250   0.6307   0.03462   0.02387  -0.0297   0.0955   1.0000
   4.500   0.6591   0.03793   0.02782  -0.0280   0.1108   1.0000
   4.750   0.6884   0.04129   0.03204  -0.0263   0.1376   1.0000
   5.000   0.7224   0.04542   0.03727  -0.0257   0.1956   1.0000
   5.250   0.7744   0.05366   0.04764  -0.0446   0.4131   1.0000
   5.500   0.7559   0.06147   0.05574  -0.0633   0.5182   1.0000
   5.750   0.7201   0.06643   0.06052  -0.0698   0.5761   1.0000
   6.000   0.6762   0.06936   0.06317  -0.0717   0.6257   1.0000
   7.000   0.7255   0.08528   0.07905  -0.0667   0.5181   1.0000
   7.250   0.7525   0.08956   0.08336  -0.0615   0.4523   1.0000
   7.500   0.7675   0.09309   0.08691  -0.0560   0.3915   1.0000
   7.750   0.7787   0.09668   0.09049  -0.0520   0.3467   1.0000
   8.000   0.7944   0.10103   0.09482  -0.0476   0.3037   1.0000
   8.250   0.7828   0.10387   0.09757  -0.0479   0.2837   1.0000
   8.500   0.7943   0.10847   0.10215  -0.0455   0.2585   1.0000
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