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GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 361 AIRFOIL (goe361-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.36 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe361-il-1000000.txt
Download as CSV file: xf-goe361-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 361 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2860   0.09340   0.09188  -0.0226   1.0000   0.0127
  -7.750  -0.2890   0.09130   0.08981  -0.0223   1.0000   0.0128
  -7.500  -0.2887   0.08889   0.08744  -0.0228   0.9993   0.0129
  -7.250  -0.2642   0.08419   0.08273  -0.0304   0.9949   0.0129
  -7.000  -0.2408   0.07969   0.07822  -0.0373   0.9893   0.0129
  -6.750  -0.2238   0.07550   0.07403  -0.0397   0.9851   0.0133
  -6.500  -0.2021   0.07252   0.07104  -0.0437   0.9772   0.0136
  -6.250  -0.1734   0.06899   0.06750  -0.0500   0.9704   0.0145
  -5.250  -0.0122   0.04793   0.04606  -0.0907   0.9077   0.0171
  -5.000   0.0090   0.04609   0.04412  -0.0922   0.8863   0.0176
  -4.750   0.0322   0.04372   0.04163  -0.0944   0.8661   0.0183
  -4.500   0.0672   0.04029   0.03801  -0.0993   0.8446   0.0207
  -4.250   0.0972   0.03684   0.03433  -0.1023   0.8188   0.0209
  -4.000   0.1252   0.03337   0.03060  -0.1044   0.7879   0.0210
  -3.750   0.1497   0.02773   0.02463  -0.1073   0.7580   0.0216
  -3.500   0.1725   0.02649   0.02319  -0.1075   0.7264   0.0220
  -3.250   0.1971   0.02518   0.02170  -0.1078   0.7031   0.0226
  -3.000   0.2235   0.02359   0.01992  -0.1083   0.6839   0.0234
  -2.750   0.2546   0.02224   0.01831  -0.1082   0.6686   0.0266
  -2.500   0.2832   0.02032   0.01609  -0.1084   0.6548   0.0269
  -2.250   0.3104   0.01860   0.01408  -0.1085   0.6418   0.0269
  -2.000   0.3359   0.01474   0.00980  -0.1090   0.6304   0.0281
  -1.750   0.3621   0.01400   0.00896  -0.1089   0.6175   0.0287
  -1.500   0.3886   0.01340   0.00823  -0.1087   0.6046   0.0295
  -1.250   0.4154   0.01283   0.00752  -0.1085   0.5918   0.0309
  -1.000   0.4426   0.01240   0.00693  -0.1082   0.5786   0.0331
  -0.750   0.4702   0.01290   0.00731  -0.1077   0.5641   0.0347
  -0.500   0.4962   0.01082   0.00496  -0.1076   0.5501   0.0377
  -0.250   0.5227   0.01054   0.00459  -0.1073   0.5330   0.0398
   0.000   0.5494   0.01036   0.00428  -0.1069   0.5146   0.0423
   0.250   0.5757   0.00998   0.00376  -0.1067   0.4956   0.0487
   0.500   0.6022   0.00983   0.00354  -0.1063   0.4771   0.0519
   0.750   0.6288   0.00970   0.00332  -0.1059   0.4603   0.0545
   1.000   0.6557   0.00888   0.00229  -0.1050   0.4461   0.0324
   1.250   0.6822   0.00872   0.00205  -0.1046   0.4321   0.0319
   1.500   0.7087   0.00863   0.00190  -0.1042   0.4191   0.0323
   1.750   0.7353   0.00860   0.00181  -0.1039   0.4068   0.0333
   2.000   0.7619   0.00862   0.00177  -0.1036   0.3948   0.0339
   2.250   0.7884   0.00866   0.00176  -0.1032   0.3825   0.0344
   2.500   0.8150   0.00871   0.00177  -0.1029   0.3702   0.0347
   2.750   0.8416   0.00875   0.00177  -0.1026   0.3577   0.0356
   3.000   0.8681   0.00884   0.00179  -0.1023   0.3449   0.0374
   3.250   0.8944   0.00895   0.00185  -0.1019   0.3316   0.0394
   3.500   0.9207   0.00907   0.00194  -0.1016   0.3182   0.0541
   3.750   0.9511   0.00771   0.00235  -0.1029   0.3050   1.0000
   4.000   0.9770   0.00792   0.00248  -0.1025   0.2923   1.0000
   4.250   1.0026   0.00817   0.00262  -0.1021   0.2757   1.0000
   4.500   1.0283   0.00839   0.00278  -0.1017   0.2647   1.0000
   4.750   1.0541   0.00859   0.00295  -0.1013   0.2559   1.0000
   5.000   1.0798   0.00880   0.00311  -0.1009   0.2455   1.0000
   5.250   1.1054   0.00903   0.00329  -0.1005   0.2363   1.0000
   5.500   1.1307   0.00927   0.00348  -0.1001   0.2262   1.0000
   5.750   1.1560   0.00952   0.00368  -0.0997   0.2134   1.0000
   6.000   1.1803   0.00986   0.00393  -0.0991   0.1908   1.0000
   6.250   1.1875   0.01228   0.00541  -0.0962   0.0292   1.0000
   6.500   1.2107   0.01277   0.00590  -0.0954   0.0213   1.0000
   6.750   1.2345   0.01316   0.00634  -0.0947   0.0187   1.0000
   7.000   1.2582   0.01355   0.00676  -0.0940   0.0170   1.0000
   7.250   1.2809   0.01405   0.00729  -0.0932   0.0153   1.0000
   7.500   1.3017   0.01477   0.00811  -0.0920   0.0139   1.0000
   7.750   1.3245   0.01520   0.00857  -0.0912   0.0133   1.0000
   8.000   1.3466   0.01569   0.00912  -0.0903   0.0125   1.0000
   8.250   1.3686   0.01616   0.00962  -0.0895   0.0117   1.0000
   8.500   1.3892   0.01675   0.01025  -0.0884   0.0109   1.0000
   8.750   1.4032   0.01796   0.01158  -0.0864   0.0101   1.0000
   9.000   1.4186   0.01893   0.01264  -0.0845   0.0098   1.0000
   9.250   1.4374   0.01954   0.01332  -0.0832   0.0094   1.0000
   9.500   1.4534   0.02034   0.01419  -0.0815   0.0091   1.0000
   9.750   1.4672   0.02122   0.01515  -0.0795   0.0088   1.0000
  10.000   1.4809   0.02205   0.01604  -0.0775   0.0085   1.0000
  10.250   1.4907   0.02294   0.01700  -0.0749   0.0082   1.0000
  10.500   1.4984   0.02378   0.01790  -0.0720   0.0079   1.0000
  10.750   1.5076   0.02456   0.01872  -0.0694   0.0076   1.0000
  11.000   1.5104   0.02575   0.01998  -0.0663   0.0073   1.0000
  11.250   1.5039   0.02768   0.02201  -0.0625   0.0071   1.0000
  11.500   1.4863   0.03082   0.02529  -0.0585   0.0069   1.0000
  11.750   1.4852   0.03297   0.02754  -0.0564   0.0068   1.0000
  12.000   1.4897   0.03472   0.02938  -0.0551   0.0067   1.0000
  12.250   1.4938   0.03663   0.03139  -0.0540   0.0066   1.0000
  12.500   1.4936   0.03914   0.03400  -0.0529   0.0065   1.0000
  12.750   1.4947   0.04165   0.03661  -0.0522   0.0064   1.0000
  13.000   1.4943   0.04445   0.03953  -0.0517   0.0063   1.0000
  13.250   1.4934   0.04743   0.04262  -0.0512   0.0062   1.0000
  13.500   1.4924   0.05051   0.04581  -0.0510   0.0061   1.0000
  13.750   1.4906   0.05378   0.04919  -0.0509   0.0060   1.0000
  14.000   1.4885   0.05716   0.05269  -0.0509   0.0059   1.0000
  14.250   1.4868   0.06058   0.05621  -0.0514   0.0058   1.0000
  14.500   1.4834   0.06433   0.06008  -0.0517   0.0057   1.0000
  14.750   1.4799   0.06821   0.06408  -0.0525   0.0056   1.0000
  15.000   1.4750   0.07242   0.06843  -0.0533   0.0055   1.0000
  15.250   1.4696   0.07686   0.07300  -0.0544   0.0055   1.0000
  15.500   1.4664   0.08108   0.07730  -0.0562   0.0054   1.0000
  15.750   1.4591   0.08609   0.08244  -0.0579   0.0053   1.0000
  16.000   1.4515   0.09131   0.08780  -0.0599   0.0053   1.0000
  16.250   1.4467   0.09622   0.09281  -0.0624   0.0052   1.0000
  16.500   1.4385   0.10186   0.09857  -0.0649   0.0051   1.0000
  16.750   1.4285   0.10796   0.10481  -0.0677   0.0051   1.0000
  17.000   1.4203   0.11383   0.11080  -0.0707   0.0051   1.0000
  17.250   1.4106   0.12017   0.11727  -0.0740   0.0050   1.0000
  17.500   1.3996   0.12694   0.12417  -0.0777   0.0050   1.0000
  17.750   1.3881   0.13393   0.13130  -0.0817   0.0050   1.0000
  18.000   1.3778   0.14083   0.13832  -0.0858   0.0049   1.0000
  18.250   1.3659   0.14829   0.14590  -0.0903   0.0049   1.0000
  18.500   1.3550   0.15567   0.15341  -0.0950   0.0049   1.0000
  18.750   1.3373   0.16509   0.16300  -0.1009   0.0049   1.0000
  19.000   1.3129   0.17684   0.17495  -0.1085   0.0050   1.0000
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