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GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 515 AIRFOIL (goe515-il)
Reynolds number: 100,000
Max Cl/Cd: 56.78 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe515-il-100000.txt
Download as CSV file: xf-goe515-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 515 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4139   0.09289   0.08778  -0.0294   1.0000   0.1189
  -8.250  -0.4278   0.09065   0.08565  -0.0313   1.0000   0.1227
  -8.000  -0.4565   0.08895   0.08413  -0.0345   1.0000   0.1240
  -7.750  -0.4778   0.08596   0.08119  -0.0392   1.0000   0.1248
  -7.500  -0.4388   0.08174   0.07695  -0.0293   1.0000   0.1299
  -7.250  -0.4431   0.07917   0.07444  -0.0291   1.0000   0.1344
  -7.000  -0.4690   0.07672   0.07202  -0.0342   1.0000   0.1388
  -6.750  -0.4725   0.07279   0.06813  -0.0329   1.0000   0.1407
  -6.500  -0.4651   0.07029   0.06569  -0.0287   1.0000   0.1432
  -6.250  -0.4649   0.06793   0.06334  -0.0267   1.0000   0.1471
  -6.000  -0.4771   0.06440   0.05960  -0.0305   1.0000   0.1551
  -5.750  -0.4702   0.06178   0.05709  -0.0266   1.0000   0.1575
  -5.250  -0.4621   0.04463   0.03877  -0.0329   1.0000   0.1112
  -5.000  -0.4494   0.04112   0.03511  -0.0317   1.0000   0.1058
  -4.750  -0.4365   0.03671   0.03025  -0.0309   1.0000   0.1031
  -4.500  -0.4211   0.03349   0.02652  -0.0299   1.0000   0.1055
  -4.250  -0.4033   0.03053   0.02298  -0.0288   1.0000   0.1072
  -4.000  -0.3835   0.02816   0.01992  -0.0276   1.0000   0.1094
  -3.750  -0.3643   0.02648   0.01816  -0.0267   1.0000   0.1136
  -3.500  -0.3447   0.02565   0.01714  -0.0256   1.0000   0.1208
  -3.250  -0.3239   0.02417   0.01530  -0.0246   1.0000   0.1272
  -3.000  -0.3036   0.02337   0.01438  -0.0235   1.0000   0.1354
  -2.750  -0.2838   0.02270   0.01361  -0.0225   1.0000   0.1465
  -2.500  -0.2637   0.02208   0.01286  -0.0215   1.0000   0.1587
  -2.250  -0.2311   0.02167   0.01237  -0.0229   0.9961   0.1740
  -2.000  -0.1943   0.02152   0.01219  -0.0252   0.9899   0.1921
  -1.750  -0.1549   0.02141   0.01202  -0.0279   0.9838   0.2095
  -1.500  -0.1205   0.02116   0.01177  -0.0296   0.9767   0.2237
  -1.250  -0.0796   0.02100   0.01160  -0.0325   0.9706   0.2387
  -1.000  -0.0468   0.02075   0.01141  -0.0338   0.9625   0.2537
  -0.750  -0.0039   0.02058   0.01130  -0.0370   0.9561   0.2750
  -0.500   0.0284   0.02022   0.01115  -0.0381   0.9467   0.3046
  -0.250   0.1205   0.01771   0.01093  -0.0506   0.9474   1.0000
   0.000   0.1686   0.01797   0.01090  -0.0546   0.9389   1.0000
   0.250   0.2090   0.01812   0.01090  -0.0571   0.9285   1.0000
   0.500   0.2462   0.01828   0.01094  -0.0590   0.9179   1.0000
   0.750   0.2982   0.01833   0.01091  -0.0636   0.9113   1.0000
   1.000   0.3290   0.01846   0.01100  -0.0642   0.8998   1.0000
   1.250   0.3667   0.01854   0.01105  -0.0660   0.8902   1.0000
   1.500   0.4172   0.01841   0.01092  -0.0701   0.8832   1.0000
   1.750   0.4503   0.01846   0.01098  -0.0709   0.8720   1.0000
   2.000   0.4952   0.01825   0.01081  -0.0736   0.8642   1.0000
   2.250   0.5320   0.01810   0.01071  -0.0748   0.8537   1.0000
   2.500   0.5626   0.01806   0.01071  -0.0747   0.8416   1.0000
   2.750   0.5959   0.01790   0.01063  -0.0750   0.8298   1.0000
   3.000   0.6308   0.01754   0.01034  -0.0752   0.8165   1.0000
   3.250   0.6625   0.01709   0.00996  -0.0744   0.8000   1.0000
   3.500   0.6927   0.01661   0.00953  -0.0733   0.7818   1.0000
   3.750   0.7220   0.01621   0.00916  -0.0721   0.7637   1.0000
   4.000   0.7468   0.01597   0.00897  -0.0703   0.7430   1.0000
   4.250   0.7714   0.01574   0.00880  -0.0685   0.7206   1.0000
   4.500   0.7954   0.01560   0.00870  -0.0668   0.6973   1.0000
   4.750   0.8207   0.01547   0.00858  -0.0652   0.6731   1.0000
   5.000   0.8431   0.01545   0.00860  -0.0633   0.6443   1.0000
   5.250   0.8635   0.01548   0.00860  -0.0609   0.6080   1.0000
   5.500   0.8826   0.01560   0.00862  -0.0584   0.5655   1.0000
   5.750   0.9000   0.01585   0.00877  -0.0557   0.5181   1.0000
   6.000   0.9159   0.01629   0.00899  -0.0529   0.4656   1.0000
   6.250   0.9287   0.01699   0.00942  -0.0498   0.4029   1.0000
   6.500   0.9381   0.01798   0.01003  -0.0463   0.3287   1.0000
   6.750   0.9459   0.01921   0.01079  -0.0429   0.2506   1.0000
   7.000   0.9536   0.02069   0.01177  -0.0397   0.1917   1.0000
   7.250   0.9614   0.02248   0.01317  -0.0366   0.1503   1.0000
   7.500   0.9722   0.02422   0.01470  -0.0339   0.1204   1.0000
   7.750   0.9863   0.02593   0.01622  -0.0318   0.1005   1.0000
   8.000   1.0040   0.02750   0.01776  -0.0301   0.0863   1.0000
   8.250   1.0244   0.02918   0.01934  -0.0289   0.0766   1.0000
   8.500   1.0457   0.03083   0.02119  -0.0276   0.0692   1.0000
   8.750   1.0724   0.03341   0.02367  -0.0277   0.0641   1.0000
   9.000   1.0945   0.03580   0.02643  -0.0264   0.0613   1.0000
   9.250   1.1123   0.03796   0.02891  -0.0248   0.0580   1.0000
   9.500   1.1291   0.04012   0.03123  -0.0234   0.0550   1.0000
   9.750   1.1451   0.04326   0.03460  -0.0220   0.0537   1.0000
  10.000   1.1564   0.04699   0.03866  -0.0202   0.0532   1.0000
  10.250   1.1621   0.05078   0.04284  -0.0177   0.0530   1.0000
  10.500   1.1633   0.05456   0.04700  -0.0150   0.0529   1.0000
  10.750   1.1600   0.05859   0.05140  -0.0122   0.0527   1.0000
  11.000   1.1517   0.06282   0.05594  -0.0094   0.0525   1.0000
  11.250   1.1407   0.06620   0.05961  -0.0062   0.0526   1.0000
  11.500   1.1246   0.06888   0.06254  -0.0025   0.0528   1.0000
  11.750   1.1031   0.07158   0.06550   0.0008   0.0532   1.0000
  12.000   1.0149   0.08011   0.07469   0.0013   0.0590   1.0000
  12.250   0.9867   0.08671   0.08143  -0.0011   0.0605   1.0000
  12.500   0.9632   0.09373   0.08853  -0.0044   0.0617   1.0000
  12.750   0.9451   0.10101   0.09586  -0.0079   0.0627   1.0000
  13.000   0.7137   0.12935   0.12454  -0.0254   0.0858   1.0000
  13.250   0.7342   0.13152   0.12678  -0.0229   0.0888   1.0000
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