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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 500,000
Max Cl/Cd: 88.15 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe100-il-500000.txt
Download as CSV file: xf-goe100-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3935   0.09358   0.09143  -0.0217   1.0000   0.0129
  -7.750  -0.3954   0.09075   0.08864  -0.0219   1.0000   0.0129
  -6.500  -0.4171   0.07305   0.07111  -0.0242   1.0000   0.0136
  -6.250  -0.4048   0.06969   0.06773  -0.0263   0.9987   0.0142
  -6.000  -0.3787   0.06587   0.06387  -0.0312   0.9964   0.0150
  -5.750  -0.3483   0.06172   0.05965  -0.0373   0.9944   0.0170
  -5.500  -0.3134   0.05634   0.05416  -0.0445   0.9909   0.0195
  -5.250  -0.2698   0.05169   0.04935  -0.0512   0.9879   0.0208
  -5.000  -0.2340   0.04625   0.04372  -0.0564   0.9855   0.0210
  -4.750  -0.2066   0.03798   0.03521  -0.0624   0.9834   0.0226
  -4.500  -0.1773   0.03533   0.03244  -0.0646   0.9801   0.0239
  -4.250  -0.1443   0.03181   0.02872  -0.0671   0.9764   0.0261
  -4.000  -0.1064   0.01659   0.01181  -0.0685   0.9740   0.0135
  -3.750  -0.0709   0.01350   0.00815  -0.0699   0.9724   0.0141
  -3.500  -0.0340   0.01201   0.00641  -0.0717   0.9709   0.0156
  -3.250   0.0033   0.01131   0.00562  -0.0736   0.9689   0.0180
  -3.000   0.0350   0.01046   0.00464  -0.0741   0.9625   0.0197
  -2.750   0.0712   0.00950   0.00353  -0.0755   0.9577   0.0237
  -2.500   0.1016   0.00907   0.00317  -0.0757   0.9495   0.0379
  -2.250   0.1340   0.00899   0.00306  -0.0765   0.9437   0.0554
  -2.000   0.1620   0.00869   0.00275  -0.0764   0.9350   0.0633
  -1.750   0.1913   0.00853   0.00251  -0.0765   0.9268   0.0691
  -1.500   0.2193   0.00828   0.00225  -0.0763   0.9163   0.0781
  -1.250   0.2462   0.00814   0.00205  -0.0759   0.9041   0.0830
  -1.000   0.2732   0.00795   0.00190  -0.0755   0.8929   0.0968
  -0.750   0.3001   0.00776   0.00186  -0.0752   0.8821   0.1570
  -0.500   0.3271   0.00766   0.00179  -0.0749   0.8709   0.1879
  -0.250   0.3540   0.00756   0.00172  -0.0746   0.8590   0.2132
   0.000   0.3806   0.00737   0.00168  -0.0743   0.8459   0.2712
   0.250   0.3960   0.00574   0.00175  -0.0718   0.8319   0.8662
   0.500   0.4390   0.00558   0.00167  -0.0745   0.8137   1.0000
   0.750   0.4644   0.00564   0.00161  -0.0738   0.7926   1.0000
   1.000   0.4898   0.00572   0.00157  -0.0731   0.7664   1.0000
   1.250   0.5148   0.00584   0.00154  -0.0724   0.7303   1.0000
   1.500   0.5381   0.00611   0.00152  -0.0712   0.6693   1.0000
   1.750   0.5598   0.00658   0.00159  -0.0699   0.5876   1.0000
   2.000   0.5828   0.00704   0.00171  -0.0690   0.5237   1.0000
   2.250   0.6070   0.00741   0.00185  -0.0684   0.4751   1.0000
   2.500   0.6317   0.00776   0.00199  -0.0678   0.4284   1.0000
   2.750   0.6548   0.00831   0.00219  -0.0671   0.3574   1.0000
   3.000   0.6782   0.00885   0.00238  -0.0665   0.2951   1.0000
   3.250   0.7030   0.00924   0.00256  -0.0661   0.2559   1.0000
   3.500   0.7278   0.00963   0.00274  -0.0657   0.2166   1.0000
   3.750   0.7523   0.01008   0.00297  -0.0653   0.1763   1.0000
   4.000   0.7766   0.01056   0.00322  -0.0648   0.1377   1.0000
   4.250   0.7955   0.01188   0.00389  -0.0636   0.0259   1.0000
   4.500   0.8216   0.01214   0.00421  -0.0632   0.0191   1.0000
   4.750   0.8473   0.01248   0.00464  -0.0628   0.0173   1.0000
   5.000   0.8724   0.01292   0.00520  -0.0622   0.0152   1.0000
   5.250   0.8970   0.01347   0.00591  -0.0615   0.0141   1.0000
   5.500   0.9205   0.01420   0.00678  -0.0606   0.0136   1.0000
   5.750   0.9439   0.01491   0.00757  -0.0598   0.0137   1.0000
   6.000   0.9679   0.01550   0.00822  -0.0590   0.0145   1.0000
   6.250   0.9932   0.01591   0.00873  -0.0582   0.0164   1.0000
   6.500   1.0129   0.01705   0.00998  -0.0568   0.0152   1.0000
   6.750   1.0361   0.01776   0.01083  -0.0556   0.0172   1.0000
   7.000   1.0559   0.01899   0.01215  -0.0538   0.0189   1.0000
   7.250   1.0752   0.02037   0.01361  -0.0522   0.0184   1.0000
   7.500   1.0946   0.02185   0.01516  -0.0507   0.0170   1.0000
   7.750   1.1139   0.02365   0.01699  -0.0494   0.0156   1.0000
   8.000   1.1343   0.02599   0.01930  -0.0484   0.0144   1.0000
   8.250   1.1570   0.03302   0.02639  -0.0483   0.0127   1.0000
   8.500   1.1747   0.03492   0.02853  -0.0467   0.0126   1.0000
   8.750   1.1896   0.03619   0.03010  -0.0447   0.0125   1.0000
   9.000   1.2047   0.03564   0.02979  -0.0425   0.0117   1.0000
   9.250   1.2197   0.03686   0.03123  -0.0406   0.0109   1.0000
   9.500   1.2323   0.03871   0.03330  -0.0385   0.0104   1.0000
   9.750   1.2420   0.04088   0.03569  -0.0363   0.0099   1.0000
  10.000   1.2484   0.04325   0.03829  -0.0338   0.0095   1.0000
  10.250   1.2514   0.04577   0.04103  -0.0311   0.0093   1.0000
  10.500   1.2509   0.04837   0.04384  -0.0282   0.0090   1.0000
  10.750   1.2450   0.05091   0.04658  -0.0247   0.0089   1.0000
  11.000   1.2347   0.05344   0.04929  -0.0210   0.0088   1.0000
  11.250   1.2227   0.05626   0.05227  -0.0180   0.0087   1.0000
  11.500   1.2096   0.05942   0.05560  -0.0159   0.0086   1.0000
  11.750   1.1954   0.06300   0.05935  -0.0148   0.0085   1.0000
  12.000   1.1803   0.06706   0.06357  -0.0146   0.0084   1.0000
  12.250   1.1640   0.07168   0.06836  -0.0155   0.0084   1.0000
  12.500   1.1469   0.07704   0.07388  -0.0177   0.0084   1.0000
  12.750   1.1293   0.08321   0.08022  -0.0213   0.0085   1.0000
  13.000   1.1110   0.09042   0.08759  -0.0262   0.0085   1.0000
  13.250   1.0921   0.09861   0.09594  -0.0322   0.0086   1.0000
  13.500   1.0725   0.10779   0.10528  -0.0388   0.0088   1.0000
  13.750   1.0526   0.11778   0.11541  -0.0458   0.0090   1.0000
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