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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.05 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe100-il-1000000-n5.txt
Download as CSV file: xf-goe100-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2915   0.10113   0.09963  -0.0244   1.0000   0.0033
  -9.500  -0.2903   0.09776   0.09628  -0.0247   1.0000   0.0034
  -7.000  -0.3551   0.07629   0.07483  -0.0341   0.9926   0.0023
  -6.750  -0.3333   0.07111   0.06963  -0.0415   0.9887   0.0022
  -6.500  -0.3103   0.06571   0.06420  -0.0487   0.9836   0.0022
  -6.000  -0.2580   0.05402   0.05238  -0.0628   0.9700   0.0020
  -5.750  -0.2292   0.04739   0.04563  -0.0692   0.9613   0.0021
  -5.500  -0.1984   0.03941   0.03744  -0.0753   0.9513   0.0022
  -5.250  -0.1733   0.01785   0.01469  -0.0805   0.9365   0.0023
  -5.000  -0.1476   0.01458   0.01082  -0.0804   0.9262   0.0024
  -4.750  -0.1211   0.01316   0.00905  -0.0801   0.9154   0.0025
  -4.500  -0.0950   0.01154   0.00705  -0.0798   0.9054   0.0028
  -4.250  -0.0681   0.01093   0.00631  -0.0797   0.8968   0.0030
  -4.000  -0.0412   0.01010   0.00526  -0.0794   0.8876   0.0032
  -3.750  -0.0141   0.00941   0.00437  -0.0791   0.8767   0.0033
  -3.500   0.0127   0.00889   0.00367  -0.0787   0.8628   0.0035
  -3.250   0.0397   0.00847   0.00310  -0.0783   0.8476   0.0040
  -3.000   0.0670   0.00818   0.00268  -0.0781   0.8349   0.0044
  -2.750   0.0946   0.00781   0.00219  -0.0779   0.8248   0.0052
  -2.500   0.1221   0.00763   0.00194  -0.0778   0.8145   0.0066
  -2.250   0.1496   0.00749   0.00170  -0.0777   0.8006   0.0080
  -2.000   0.1768   0.00732   0.00142  -0.0774   0.7794   0.0130
  -1.750   0.2036   0.00720   0.00130  -0.0772   0.7535   0.0382
  -1.500   0.2306   0.00723   0.00123  -0.0770   0.7270   0.0449
  -1.250   0.2572   0.00727   0.00114  -0.0767   0.6909   0.0504
  -1.000   0.2827   0.00749   0.00110  -0.0762   0.6298   0.0540
  -0.750   0.3081   0.00775   0.00108  -0.0758   0.5651   0.0551
  -0.500   0.3345   0.00792   0.00107  -0.0756   0.5219   0.0581
  -0.250   0.3609   0.00808   0.00106  -0.0754   0.4797   0.0639
   0.250   0.4136   0.00831   0.00114  -0.0751   0.3945   0.1316
   0.500   0.4402   0.00848   0.00119  -0.0750   0.3593   0.1456
   0.750   0.4672   0.00860   0.00124  -0.0750   0.3342   0.1574
   1.000   0.4942   0.00872   0.00129  -0.0749   0.3135   0.1688
   1.250   0.5213   0.00880   0.00135  -0.0749   0.2954   0.1860
   1.500   0.5484   0.00887   0.00142  -0.0748   0.2788   0.2136
   1.750   0.5752   0.00875   0.00155  -0.0749   0.2614   0.3525
   2.000   0.5976   0.00769   0.00171  -0.0744   0.2449   0.8450
   2.250   0.6235   0.00766   0.00183  -0.0738   0.2105   1.0000
   2.500   0.6496   0.00793   0.00195  -0.0736   0.1859   1.0000
   2.750   0.6760   0.00814   0.00207  -0.0735   0.1692   1.0000
   3.000   0.7018   0.00845   0.00224  -0.0732   0.1431   1.0000
   3.250   0.7268   0.00886   0.00245  -0.0729   0.1065   1.0000
   3.500   0.7486   0.00978   0.00299  -0.0720   0.0152   1.0000
   3.750   0.7753   0.00997   0.00320  -0.0718   0.0102   1.0000
   4.000   0.8018   0.01019   0.00347  -0.0716   0.0081   1.0000
   4.250   0.8280   0.01046   0.00377  -0.0713   0.0060   1.0000
   4.500   0.8541   0.01072   0.00407  -0.0711   0.0050   1.0000
   4.750   0.8795   0.01110   0.00449  -0.0707   0.0042   1.0000
   5.000   0.9046   0.01155   0.00502  -0.0702   0.0037   1.0000
   5.250   0.9302   0.01186   0.00535  -0.0699   0.0030   1.0000
   5.500   0.9553   0.01226   0.00578  -0.0695   0.0027   1.0000
   5.750   0.9787   0.01296   0.00657  -0.0687   0.0023   1.0000
   6.000   1.0020   0.01365   0.00736  -0.0679   0.0021   1.0000
   6.250   1.0227   0.01470   0.00856  -0.0666   0.0019   1.0000
   6.500   1.0411   0.01602   0.00998  -0.0648   0.0018   1.0000
   6.750   1.0590   0.01743   0.01145  -0.0629   0.0018   1.0000
   7.000   1.0777   0.01892   0.01298  -0.0612   0.0018   1.0000
   7.250   1.0979   0.02043   0.01454  -0.0598   0.0018   1.0000
   7.500   1.1196   0.02170   0.01587  -0.0587   0.0016   1.0000
   7.750   1.1409   0.02268   0.01692  -0.0578   0.0014   1.0000
   8.000   1.1611   0.02367   0.01800  -0.0569   0.0013   1.0000
   8.250   1.1798   0.02536   0.01980  -0.0557   0.0012   1.0000
   8.500   1.1991   0.02773   0.02232  -0.0542   0.0012   1.0000
   8.750   1.2186   0.02978   0.02458  -0.0526   0.0011   1.0000
   9.000   1.2350   0.03253   0.02759  -0.0504   0.0009   1.0000
   9.250   1.2474   0.03527   0.03059  -0.0479   0.0008   1.0000
   9.500   1.2572   0.03807   0.03363  -0.0453   0.0008   1.0000
   9.750   1.2631   0.04096   0.03677  -0.0424   0.0008   1.0000
  10.000   1.2648   0.04388   0.03994  -0.0392   0.0008   1.0000
  10.250   1.2622   0.04682   0.04312  -0.0357   0.0008   1.0000
  10.500   1.2543   0.04966   0.04619  -0.0317   0.0008   1.0000
  10.750   1.2404   0.05217   0.04888  -0.0271   0.0008   1.0000
  11.000   1.2248   0.05502   0.05190  -0.0235   0.0008   1.0000
  11.250   1.2081   0.05831   0.05536  -0.0209   0.0008   1.0000
  11.500   1.1909   0.06208   0.05929  -0.0196   0.0008   1.0000
  11.750   1.1735   0.06640   0.06377  -0.0196   0.0009   1.0000
  12.000   1.1560   0.07135   0.06887  -0.0208   0.0009   1.0000
  12.250   1.1383   0.07703   0.07469  -0.0234   0.0009   1.0000
  12.500   1.1205   0.08365   0.08145  -0.0274   0.0009   1.0000
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