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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 100,000
Max Cl/Cd: 27.56 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe05k-il-100000-n5.txt
Download as CSV file: xf-goe05k-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5253   0.10087   0.09587  -0.0112   1.0000   0.0274
  -8.000  -0.5252   0.09817   0.09323  -0.0130   1.0000   0.0278
  -7.750  -0.5265   0.09550   0.09064  -0.0147   1.0000   0.0280
  -7.500  -0.5236   0.09244   0.08761  -0.0178   1.0000   0.0281
  -7.250  -0.5175   0.08909   0.08430  -0.0219   1.0000   0.0283
  -7.000  -0.5090   0.08559   0.08077  -0.0255   1.0000   0.0284
  -6.750  -0.5100   0.08052   0.07580  -0.0210   1.0000   0.0298
  -6.500  -0.5035   0.07691   0.07219  -0.0218   1.0000   0.0312
  -6.250  -0.4946   0.07321   0.06848  -0.0238   1.0000   0.0328
  -6.000  -0.4827   0.06936   0.06458  -0.0266   1.0000   0.0349
  -5.750  -0.4615   0.06575   0.06076  -0.0320   1.0000   0.0367
  -5.250  -0.4412   0.05766   0.05263  -0.0319   1.0000   0.0398
  -5.000  -0.4113   0.05609   0.05048  -0.0352   1.0000   0.0446
  -4.750  -0.4041   0.05036   0.04490  -0.0346   1.0000   0.0464
  -4.500  -0.3895   0.04683   0.04130  -0.0342   1.0000   0.0498
  -4.250  -0.3649   0.04405   0.03802  -0.0352   1.0000   0.0571
  -4.000  -0.3500   0.04023   0.03421  -0.0346   1.0000   0.0605
  -3.750  -0.3283   0.03742   0.03102  -0.0345   1.0000   0.0706
  -3.250  -0.2753   0.03029   0.02313  -0.0319   1.0000   0.0246
  -3.000  -0.2472   0.02803   0.02026  -0.0301   1.0000   0.0186
  -2.750  -0.2239   0.02536   0.01723  -0.0292   1.0000   0.0171
  -2.500  -0.1992   0.02327   0.01470  -0.0281   1.0000   0.0172
  -2.250  -0.1738   0.02143   0.01243  -0.0269   1.0000   0.0177
  -2.000  -0.1482   0.01945   0.01011  -0.0259   1.0000   0.0175
  -1.750  -0.1228   0.01782   0.00823  -0.0248   1.0000   0.0176
  -1.500  -0.0984   0.01613   0.00639  -0.0238   1.0000   0.0200
  -1.250  -0.0751   0.01509   0.00522  -0.0228   1.0000   0.0238
  -1.000  -0.0509   0.01428   0.00419  -0.0218   1.0000   0.0324
  -0.750  -0.0008   0.01071   0.00326  -0.0261   1.0000   1.0000
  -0.500   0.0219   0.01078   0.00291  -0.0252   1.0000   1.0000
  -0.250   0.0445   0.01086   0.00274  -0.0243   1.0000   1.0000
   0.000   0.0669   0.01096   0.00265  -0.0234   1.0000   1.0000
   0.250   0.0893   0.01107   0.00263  -0.0226   1.0000   1.0000
   0.500   0.1116   0.01120   0.00265  -0.0218   1.0000   1.0000
   0.750   0.1339   0.01134   0.00274  -0.0210   1.0000   1.0000
   1.000   0.1560   0.01150   0.00289  -0.0203   1.0000   1.0000
   1.250   0.1781   0.01167   0.00310  -0.0195   1.0000   1.0000
   1.500   0.1998   0.01187   0.00336  -0.0187   1.0000   1.0000
   1.750   0.2216   0.01209   0.00368  -0.0180   1.0000   1.0000
   2.000   0.2612   0.01238   0.00420  -0.0210   0.9925   1.0000
   2.250   0.3001   0.01266   0.00486  -0.0238   0.9850   1.0000
   2.500   0.3403   0.01289   0.00554  -0.0267   0.9759   1.0000
   2.750   0.4660   0.01691   0.00646  -0.0413   0.0185   1.0000
   3.000   0.4874   0.01830   0.00799  -0.0395   0.0164   1.0000
   3.250   0.5102   0.02014   0.00990  -0.0383   0.0141   1.0000
   3.500   0.5363   0.02243   0.01236  -0.0373   0.0139   1.0000
   3.750   0.5635   0.02445   0.01472  -0.0361   0.0144   1.0000
   4.000   0.5907   0.02697   0.01781  -0.0344   0.0160   1.0000
   4.250   0.6145   0.02997   0.02126  -0.0327   0.0177   1.0000
   4.500   0.6340   0.03396   0.02563  -0.0312   0.0193   1.0000
   4.750   0.6616   0.03581   0.02811  -0.0286   0.0240   1.0000
   5.000   0.6808   0.03964   0.03228  -0.0268   0.0290   1.0000
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