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GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 615 AIRFOIL (goe615-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.5 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe615-il-1000000.txt
Download as CSV file: xf-goe615-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 615 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1633   0.08549   0.08373  -0.0804   0.9597   0.0289
 -10.000  -0.1537   0.07909   0.07732  -0.0869   0.9516   0.0292
  -9.750  -0.1230   0.07680   0.07499  -0.0919   0.9434   0.0295
  -9.500  -0.0899   0.07348   0.07163  -0.0989   0.9353   0.0299
  -9.250  -0.0545   0.06946   0.06754  -0.1078   0.9254   0.0305
  -9.000  -0.3098   0.02026   0.01604  -0.1305   0.8489   0.0289
  -8.500  -0.2773   0.01730   0.01270  -0.1277   0.8321   0.0297
  -8.250  -0.2545   0.01683   0.01213  -0.1269   0.8243   0.0300
  -8.000  -0.2309   0.01639   0.01162  -0.1261   0.8170   0.0304
  -7.750  -0.2075   0.01592   0.01106  -0.1253   0.8092   0.0307
  -7.500  -0.1838   0.01541   0.01045  -0.1245   0.8021   0.0311
  -7.250  -0.1603   0.01483   0.00977  -0.1237   0.7942   0.0315
  -7.000  -0.1364   0.01433   0.00914  -0.1229   0.7866   0.0319
  -6.750  -0.1119   0.01385   0.00857  -0.1222   0.7786   0.0324
  -6.250  -0.0620   0.01312   0.00762  -0.1208   0.7628   0.0331
  -6.000  -0.0368   0.01285   0.00724  -0.1201   0.7546   0.0334
  -5.750  -0.0141   0.01179   0.00611  -0.1192   0.7466   0.0340
  -5.500   0.0107   0.01144   0.00571  -0.1185   0.7377   0.0345
  -5.250   0.0365   0.01119   0.00543  -0.1179   0.7290   0.0350
  -4.750   0.0876   0.01072   0.00486  -0.1166   0.7094   0.0361
  -4.500   0.1130   0.01054   0.00461  -0.1159   0.6985   0.0367
  -4.000   0.1633   0.01025   0.00416  -0.1144   0.6696   0.0379
  -3.750   0.1884   0.01016   0.00398  -0.1136   0.6529   0.0383
  -3.500   0.2113   0.00973   0.00348  -0.1125   0.6365   0.0392
  -3.250   0.2360   0.00958   0.00327  -0.1117   0.6211   0.0400
  -3.000   0.2611   0.00950   0.00314  -0.1110   0.6068   0.0409
  -2.750   0.2863   0.00944   0.00301  -0.1103   0.5934   0.0418
  -2.500   0.3114   0.00939   0.00289  -0.1096   0.5818   0.0428
  -2.250   0.3375   0.00935   0.00280  -0.1090   0.5723   0.0437
  -2.000   0.3623   0.00919   0.00259  -0.1083   0.5638   0.0452
  -1.750   0.3883   0.00910   0.00248  -0.1077   0.5565   0.0468
  -1.500   0.4138   0.00908   0.00241  -0.1071   0.5491   0.0483
  -1.250   0.4406   0.00902   0.00234  -0.1067   0.5436   0.0499
  -1.000   0.4666   0.00893   0.00222  -0.1061   0.5383   0.0520
  -0.750   0.4922   0.00889   0.00216  -0.1055   0.5331   0.0548
  -0.500   0.5191   0.00885   0.00211  -0.1052   0.5290   0.0577
  -0.250   0.5455   0.00877   0.00205  -0.1047   0.5244   0.0628
   0.000   0.5715   0.00872   0.00201  -0.1042   0.5201   0.0720
   0.250   0.5949   0.00847   0.00202  -0.1033   0.5151   0.1659
   0.500   0.6206   0.00829   0.00205  -0.1029   0.5116   0.2376
   0.750   0.6462   0.00816   0.00208  -0.1023   0.5072   0.2949
   1.000   0.6708   0.00805   0.00214  -0.1017   0.5027   0.3650
   1.250   0.6930   0.00785   0.00223  -0.1005   0.4975   0.4876
   1.500   0.7130   0.00740   0.00231  -0.0989   0.4933   0.6781
   1.750   0.7992   0.00703   0.00256  -0.1115   0.4809   0.9881
   2.000   0.8491   0.00713   0.00262  -0.1163   0.4729   1.0000
   2.250   0.8717   0.00723   0.00267  -0.1151   0.4658   1.0000
   2.500   0.8952   0.00731   0.00271  -0.1141   0.4593   1.0000
   2.750   0.9181   0.00741   0.00277  -0.1130   0.4504   1.0000
   3.000   0.9409   0.00752   0.00283  -0.1119   0.4399   1.0000
   3.250   0.9626   0.00767   0.00290  -0.1105   0.4255   1.0000
   3.500   0.9832   0.00787   0.00300  -0.1090   0.4049   1.0000
   3.750   1.0013   0.00818   0.00315  -0.1071   0.3779   1.0000
   4.000   1.0178   0.00857   0.00337  -0.1048   0.3498   1.0000
   4.250   1.0358   0.00890   0.00358  -0.1029   0.3287   1.0000
   4.500   1.0550   0.00919   0.00377  -0.1012   0.3148   1.0000
   4.750   1.0747   0.00944   0.00396  -0.0996   0.3037   1.0000
   5.000   1.0956   0.00965   0.00413  -0.0982   0.2954   1.0000
   5.250   1.1151   0.00990   0.00432  -0.0966   0.2864   1.0000
   5.500   1.1361   0.01009   0.00449  -0.0953   0.2792   1.0000
   5.750   1.1552   0.01034   0.00470  -0.0936   0.2709   1.0000
   6.000   1.1741   0.01054   0.00487  -0.0919   0.2642   1.0000
   6.250   1.1913   0.01078   0.00507  -0.0898   0.2565   1.0000
   6.500   1.2094   0.01101   0.00527  -0.0880   0.2497   1.0000
   6.750   1.2274   0.01125   0.00549  -0.0862   0.2424   1.0000
   7.000   1.2452   0.01152   0.00572  -0.0844   0.2356   1.0000
   7.250   1.2638   0.01178   0.00596  -0.0827   0.2281   1.0000
   7.500   1.2811   0.01210   0.00624  -0.0809   0.2207   1.0000
   7.750   1.2997   0.01238   0.00650  -0.0794   0.2136   1.0000
   8.000   1.3161   0.01276   0.00684  -0.0775   0.2040   1.0000
   8.250   1.3321   0.01318   0.00720  -0.0756   0.1941   1.0000
   8.500   1.3476   0.01363   0.00760  -0.0738   0.1827   1.0000
   8.750   1.3621   0.01414   0.00805  -0.0718   0.1710   1.0000
   9.000   1.3734   0.01483   0.00864  -0.0694   0.1548   1.0000
   9.250   1.3804   0.01575   0.00942  -0.0666   0.1330   1.0000
   9.500   1.3849   0.01687   0.01039  -0.0636   0.1097   1.0000
   9.750   1.3742   0.01894   0.01219  -0.0590   0.0683   1.0000
  10.000   1.3850   0.01987   0.01310  -0.0572   0.0623   1.0000
  10.250   1.3987   0.02065   0.01390  -0.0558   0.0606   1.0000
  10.500   1.4115   0.02152   0.01478  -0.0544   0.0589   1.0000
  10.750   1.4237   0.02245   0.01574  -0.0530   0.0575   1.0000
  11.000   1.4351   0.02346   0.01677  -0.0516   0.0558   1.0000
  11.250   1.4472   0.02446   0.01780  -0.0504   0.0548   1.0000
  11.500   1.4593   0.02546   0.01885  -0.0492   0.0540   1.0000
  11.750   1.4726   0.02641   0.01984  -0.0483   0.0534   1.0000
  12.000   1.4847   0.02747   0.02094  -0.0472   0.0529   1.0000
  12.250   1.4961   0.02860   0.02213  -0.0462   0.0523   1.0000
  12.500   1.5074   0.02976   0.02333  -0.0453   0.0520   1.0000
  12.750   1.5165   0.03112   0.02474  -0.0443   0.0510   1.0000
  13.000   1.5254   0.03253   0.02619  -0.0433   0.0503   1.0000
  13.250   1.5332   0.03408   0.02779  -0.0424   0.0496   1.0000
  13.500   1.5388   0.03585   0.02960  -0.0414   0.0485   1.0000
  13.750   1.5439   0.03772   0.03153  -0.0406   0.0477   1.0000
  14.000   1.5474   0.03982   0.03369  -0.0398   0.0469   1.0000
  14.250   1.5558   0.04147   0.03540  -0.0393   0.0465   1.0000
  14.500   1.5661   0.04295   0.03693  -0.0388   0.0461   1.0000
  14.750   1.5757   0.04452   0.03855  -0.0384   0.0453   1.0000
  15.000   1.5838   0.04626   0.04034  -0.0381   0.0442   1.0000
  15.250   1.5900   0.04823   0.04234  -0.0377   0.0430   1.0000
  15.500   1.5931   0.05058   0.04473  -0.0374   0.0419   1.0000
  15.750   1.5929   0.05332   0.04751  -0.0371   0.0402   1.0000
  16.000   1.6032   0.05491   0.04915  -0.0370   0.0386   1.0000
  16.250   1.6056   0.05741   0.05165  -0.0368   0.0351   1.0000
  16.500   1.6064   0.06014   0.05440  -0.0368   0.0313   1.0000
  17.000   1.5641   0.07102   0.06530  -0.0371   0.0147   1.0000
  17.500   1.5478   0.07912   0.07359  -0.0379   0.0133   1.0000
  17.750   1.5395   0.08325   0.07781  -0.0384   0.0130   1.0000
  18.000   1.5296   0.08766   0.08232  -0.0390   0.0127   1.0000
  18.250   1.5182   0.09236   0.08712  -0.0398   0.0123   1.0000
  18.500   1.5086   0.09684   0.09169  -0.0407   0.0122   1.0000
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