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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 200,000
Max Cl/Cd: 79.06 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe517-il-200000-n5.txt
Download as CSV file: xf-goe517-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3071   0.09212   0.08886  -0.0290   1.0000   0.0189
  -7.500  -0.3116   0.09020   0.08701  -0.0278   1.0000   0.0193
  -7.250  -0.3174   0.08835   0.08523  -0.0266   0.9991   0.0193
  -7.000  -0.2975   0.08419   0.08108  -0.0329   0.9901   0.0207
  -6.750  -0.2614   0.08013   0.07698  -0.0472   0.9786   0.0232
  -6.500  -0.2357   0.07578   0.07259  -0.0538   0.9703   0.0234
  -6.250  -0.2087   0.07119   0.06795  -0.0604   0.9623   0.0235
  -6.000  -0.1804   0.06633   0.06302  -0.0666   0.9554   0.0235
  -5.500  -0.1377   0.05369   0.05021  -0.0759   0.9366   0.0160
  -5.250  -0.1122   0.04960   0.04603  -0.0799   0.9281   0.0151
  -5.000  -0.0825   0.04492   0.04117  -0.0845   0.9202   0.0144
  -4.750  -0.0543   0.04012   0.03616  -0.0880   0.9110   0.0139
  -4.500  -0.0230   0.03512   0.03088  -0.0913   0.9040   0.0145
  -4.250   0.0036   0.03000   0.02539  -0.0927   0.8945   0.0151
  -4.000   0.0307   0.02352   0.01825  -0.0936   0.8874   0.0150
  -3.750   0.0552   0.01947   0.01344  -0.0930   0.8785   0.0153
  -3.500   0.0831   0.01718   0.01054  -0.0928   0.8716   0.0160
  -3.250   0.1090   0.01574   0.00878  -0.0924   0.8632   0.0177
  -3.000   0.1371   0.01485   0.00767  -0.0923   0.8563   0.0197
  -2.750   0.1636   0.01391   0.00649  -0.0917   0.8481   0.0216
  -2.250   0.2170   0.01246   0.00473  -0.0908   0.8322   0.0302
  -2.000   0.2438   0.01201   0.00421  -0.0903   0.8240   0.0392
  -1.750   0.2702   0.01169   0.00390  -0.0898   0.8149   0.0591
  -1.500   0.2968   0.01160   0.00377  -0.0895   0.8052   0.0808
  -1.250   0.3238   0.01153   0.00361  -0.0891   0.7947   0.0967
  -1.000   0.3497   0.01145   0.00345  -0.0885   0.7818   0.1117
  -0.750   0.3752   0.01130   0.00324  -0.0879   0.7679   0.1213
  -0.500   0.4007   0.01116   0.00305  -0.0873   0.7537   0.1309
  -0.250   0.4261   0.01104   0.00287  -0.0866   0.7386   0.1417
   0.000   0.4514   0.01093   0.00272  -0.0860   0.7218   0.1547
   0.500   0.5015   0.01069   0.00251  -0.0847   0.6873   0.2216
   1.000   0.5872   0.00909   0.00241  -0.0912   0.6493   1.0000
   1.250   0.6112   0.00923   0.00239  -0.0903   0.6309   1.0000
   1.500   0.6352   0.00938   0.00240  -0.0894   0.6132   1.0000
   1.750   0.6593   0.00955   0.00243  -0.0886   0.5972   1.0000
   2.000   0.6833   0.00973   0.00249  -0.0877   0.5824   1.0000
   2.250   0.7074   0.00992   0.00257  -0.0869   0.5685   1.0000
   2.500   0.7315   0.01012   0.00268  -0.0861   0.5556   1.0000
   2.750   0.7557   0.01032   0.00281  -0.0854   0.5437   1.0000
   3.000   0.7801   0.01052   0.00296  -0.0847   0.5320   1.0000
   3.250   0.8043   0.01073   0.00314  -0.0840   0.5201   1.0000
   3.500   0.8283   0.01095   0.00331  -0.0832   0.5080   1.0000
   3.750   0.8526   0.01116   0.00351  -0.0826   0.4956   1.0000
   4.000   0.8768   0.01136   0.00373  -0.0819   0.4826   1.0000
   4.250   0.9007   0.01157   0.00395  -0.0811   0.4681   1.0000
   4.500   0.9244   0.01179   0.00418  -0.0803   0.4519   1.0000
   4.750   0.9479   0.01202   0.00444  -0.0795   0.4345   1.0000
   5.000   0.9709   0.01228   0.00470  -0.0787   0.4157   1.0000
   5.250   0.9934   0.01258   0.00498  -0.0777   0.3958   1.0000
   5.500   1.0156   0.01291   0.00531  -0.0767   0.3774   1.0000
   5.750   1.0375   0.01327   0.00567  -0.0757   0.3606   1.0000
   6.000   1.0591   0.01367   0.00607  -0.0746   0.3451   1.0000
   6.250   1.0791   0.01417   0.00652  -0.0734   0.3224   1.0000
   6.500   1.0972   0.01478   0.00699  -0.0718   0.2892   1.0000
   6.750   1.1157   0.01536   0.00747  -0.0704   0.2561   1.0000
   7.000   1.1331   0.01605   0.00800  -0.0689   0.2115   1.0000
   7.250   1.1354   0.01814   0.00922  -0.0655   0.0811   1.0000
   7.500   1.1421   0.01990   0.01062  -0.0625   0.0258   1.0000
   7.750   1.1564   0.02094   0.01175  -0.0603   0.0189   1.0000
   8.000   1.1709   0.02186   0.01281  -0.0583   0.0159   1.0000
   8.250   1.1815   0.02302   0.01412  -0.0558   0.0144   1.0000
   8.500   1.1922   0.02403   0.01530  -0.0532   0.0132   1.0000
   8.750   1.2000   0.02508   0.01647  -0.0503   0.0119   1.0000
   9.000   1.2018   0.02651   0.01798  -0.0469   0.0111   1.0000
   9.250   1.2071   0.02780   0.01941  -0.0439   0.0105   1.0000
   9.500   1.2103   0.02931   0.02105  -0.0410   0.0100   1.0000
   9.750   1.2135   0.03092   0.02279  -0.0384   0.0096   1.0000
  10.000   1.2164   0.03268   0.02466  -0.0360   0.0093   1.0000
  10.250   1.2199   0.03451   0.02659  -0.0339   0.0090   1.0000
  10.500   1.2226   0.03653   0.02865  -0.0320   0.0086   1.0000
  10.750   1.2276   0.03854   0.03084  -0.0303   0.0080   1.0000
  11.000   1.2337   0.04054   0.03302  -0.0287   0.0075   1.0000
  11.250   1.2395   0.04275   0.03538  -0.0272   0.0072   1.0000
  11.500   1.2456   0.04505   0.03784  -0.0258   0.0070   1.0000
  11.750   1.2507   0.04752   0.04048  -0.0246   0.0068   1.0000
  12.000   1.2545   0.05015   0.04328  -0.0235   0.0067   1.0000
  12.250   1.2564   0.05296   0.04627  -0.0225   0.0065   1.0000
  12.500   1.2568   0.05603   0.04953  -0.0217   0.0064   1.0000
  12.750   1.2549   0.05946   0.05315  -0.0211   0.0063   1.0000
  13.000   1.2509   0.06313   0.05704  -0.0208   0.0063   1.0000
  13.250   1.2443   0.06725   0.06137  -0.0209   0.0063   1.0000
  13.500   1.2338   0.07187   0.06624  -0.0214   0.0062   1.0000
  13.750   1.2208   0.07696   0.07159  -0.0227   0.0062   1.0000
  14.000   1.2095   0.08200   0.07685  -0.0243   0.0062   1.0000
  14.250   1.1936   0.08806   0.08317  -0.0268   0.0061   1.0000
  14.500   1.1834   0.09351   0.08876  -0.0290   0.0062   1.0000
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