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GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 500,000
Max Cl/Cd: 104.38 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe675-il-500000.txt
Download as CSV file: xf-goe675-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 675 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6090   0.03706   0.03337  -0.1456   0.9411   0.0370
 -12.750  -0.6205   0.03313   0.02913  -0.1476   0.9318   0.0371
 -12.500  -0.6168   0.03054   0.02634  -0.1480   0.9253   0.0374
 -12.250  -0.6054   0.02876   0.02440  -0.1479   0.9203   0.0377
 -12.000  -0.5901   0.02732   0.02286  -0.1477   0.9152   0.0380
 -11.750  -0.5727   0.02607   0.02149  -0.1475   0.9105   0.0383
 -11.500  -0.5542   0.02490   0.02018  -0.1472   0.9064   0.0386
 -11.250  -0.5344   0.02384   0.01897  -0.1469   0.9025   0.0390
 -11.000  -0.5137   0.02279   0.01780  -0.1467   0.8984   0.0395
 -10.750  -0.4920   0.02184   0.01670  -0.1464   0.8942   0.0400
 -10.500  -0.4694   0.02097   0.01567  -0.1461   0.8904   0.0405
 -10.250  -0.4460   0.02018   0.01471  -0.1458   0.8871   0.0410
 -10.000  -0.4219   0.01949   0.01386  -0.1455   0.8837   0.0414
  -9.750  -0.3994   0.01845   0.01276  -0.1452   0.8798   0.0420
  -9.500  -0.3749   0.01777   0.01204  -0.1449   0.8759   0.0426
  -9.250  -0.3493   0.01723   0.01145  -0.1447   0.8725   0.0433
  -9.000  -0.3232   0.01673   0.01087  -0.1446   0.8695   0.0440
  -8.750  -0.2969   0.01628   0.01032  -0.1444   0.8663   0.0449
  -8.500  -0.2707   0.01580   0.00976  -0.1442   0.8627   0.0457
  -8.250  -0.2446   0.01526   0.00916  -0.1440   0.8589   0.0467
  -8.000  -0.2179   0.01482   0.00872  -0.1439   0.8555   0.0479
  -7.750  -0.1903   0.01450   0.00835  -0.1438   0.8524   0.0494
  -7.500  -0.1625   0.01420   0.00796  -0.1437   0.8492   0.0511
  -7.250  -0.1355   0.01386   0.00763  -0.1436   0.8451   0.0531
  -7.000  -0.1078   0.01364   0.00739  -0.1435   0.8404   0.0554
  -6.750  -0.0798   0.01334   0.00704  -0.1434   0.8361   0.0583
  -6.500  -0.0510   0.01323   0.00690  -0.1434   0.8324   0.0617
  -6.250  -0.0225   0.01311   0.00675  -0.1433   0.8286   0.0657
  -6.000   0.0060   0.01310   0.00672  -0.1433   0.8241   0.0699
  -5.750   0.0343   0.01294   0.00656  -0.1433   0.8195   0.0734
  -5.500   0.0634   0.01293   0.00650  -0.1433   0.8156   0.0769
  -5.250   0.0923   0.01278   0.00626  -0.1434   0.8118   0.0802
  -5.000   0.1201   0.01267   0.00620  -0.1434   0.8070   0.0829
  -4.750   0.1486   0.01259   0.00608  -0.1433   0.8021   0.0858
  -4.500   0.1775   0.01253   0.00592  -0.1433   0.7974   0.0878
  -4.250   0.2055   0.01211   0.00550  -0.1433   0.7928   0.0905
  -4.000   0.2333   0.01196   0.00538  -0.1433   0.7874   0.0928
  -3.750   0.2618   0.01184   0.00523  -0.1433   0.7827   0.0951
  -3.500   0.2908   0.01174   0.00506  -0.1433   0.7784   0.0972
  -3.250   0.3189   0.01146   0.00477  -0.1433   0.7737   0.0997
  -3.000   0.3467   0.01128   0.00463  -0.1432   0.7680   0.1024
  -2.750   0.3752   0.01117   0.00451  -0.1432   0.7628   0.1051
  -2.500   0.4045   0.01111   0.00438  -0.1433   0.7582   0.1079
  -2.250   0.4323   0.01102   0.00429  -0.1432   0.7522   0.1094
  -2.000   0.4598   0.01068   0.00396  -0.1431   0.7462   0.1119
  -1.750   0.4884   0.01052   0.00377  -0.1431   0.7406   0.1142
  -1.500   0.5160   0.01040   0.00369  -0.1430   0.7338   0.1167
  -1.250   0.5441   0.01031   0.00357  -0.1429   0.7273   0.1195
  -1.000   0.5724   0.01024   0.00346  -0.1428   0.7208   0.1219
  -0.750   0.5997   0.01006   0.00332  -0.1426   0.7128   0.1266
  -0.500   0.6277   0.00999   0.00322  -0.1425   0.7054   0.1318
  -0.250   0.6550   0.00991   0.00316  -0.1423   0.6968   0.1382
   0.000   0.6825   0.00983   0.00308  -0.1421   0.6885   0.1498
   0.250   0.7095   0.00972   0.00305  -0.1419   0.6787   0.1687
   0.500   0.7362   0.00960   0.00302  -0.1417   0.6686   0.2063
   0.750   0.7623   0.00947   0.00308  -0.1414   0.6569   0.2739
   1.000   0.7885   0.00940   0.00312  -0.1410   0.6450   0.3286
   1.250   0.8138   0.00931   0.00318  -0.1406   0.6319   0.3996
   1.500   0.8374   0.00904   0.00330  -0.1399   0.6168   0.5616
   1.750   0.8662   0.00832   0.00349  -0.1397   0.5993   1.0000
   2.000   0.8893   0.00852   0.00357  -0.1387   0.5799   1.0000
   2.250   0.9118   0.00876   0.00368  -0.1376   0.5587   1.0000
   2.500   0.9330   0.00905   0.00382  -0.1363   0.5358   1.0000
   2.750   0.9533   0.00939   0.00399  -0.1348   0.5138   1.0000
   3.000   0.9739   0.00973   0.00419  -0.1334   0.4948   1.0000
   3.250   0.9953   0.01004   0.00439  -0.1322   0.4796   1.0000
   3.500   1.0175   0.01032   0.00459  -0.1312   0.4677   1.0000
   3.750   1.0389   0.01064   0.00482  -0.1300   0.4575   1.0000
   4.000   1.0615   0.01091   0.00503  -0.1290   0.4485   1.0000
   4.250   1.0827   0.01123   0.00527  -0.1278   0.4407   1.0000
   4.500   1.1060   0.01146   0.00548  -0.1270   0.4341   1.0000
   4.750   1.1266   0.01176   0.00572  -0.1257   0.4275   1.0000
   5.000   1.1473   0.01205   0.00597  -0.1245   0.4216   1.0000
   5.250   1.1694   0.01228   0.00620  -0.1234   0.4158   1.0000
   5.500   1.1893   0.01262   0.00649  -0.1221   0.4091   1.0000
   5.750   1.2101   0.01293   0.00677  -0.1209   0.4026   1.0000
   6.000   1.2315   0.01319   0.00704  -0.1199   0.3960   1.0000
   6.250   1.2511   0.01357   0.00736  -0.1186   0.3900   1.0000
   6.500   1.2725   0.01388   0.00767  -0.1176   0.3849   1.0000
   6.750   1.2942   0.01415   0.00797  -0.1167   0.3796   1.0000
   7.000   1.3142   0.01452   0.00831  -0.1155   0.3740   1.0000
   7.250   1.3338   0.01493   0.00870  -0.1143   0.3687   1.0000
   7.500   1.3555   0.01520   0.00902  -0.1135   0.3637   1.0000
   7.750   1.3757   0.01557   0.00940  -0.1124   0.3584   1.0000
   8.000   1.3940   0.01606   0.00984  -0.1111   0.3533   1.0000
   8.250   1.4149   0.01640   0.01023  -0.1102   0.3484   1.0000
   8.500   1.4345   0.01679   0.01065  -0.1092   0.3422   1.0000
   8.750   1.4502   0.01740   0.01120  -0.1076   0.3351   1.0000
   9.000   1.4708   0.01776   0.01163  -0.1068   0.3283   1.0000
   9.250   1.4880   0.01831   0.01217  -0.1055   0.3217   1.0000
   9.500   1.5055   0.01886   0.01273  -0.1043   0.3157   1.0000
   9.750   1.5239   0.01938   0.01328  -0.1032   0.3086   1.0000
  10.000   1.5383   0.02011   0.01399  -0.1017   0.3014   1.0000
  10.250   1.5567   0.02065   0.01457  -0.1007   0.2937   1.0000
  10.500   1.5697   0.02149   0.01538  -0.0991   0.2848   1.0000
  10.750   1.5856   0.02219   0.01610  -0.0978   0.2752   1.0000
  11.000   1.5988   0.02306   0.01696  -0.0963   0.2657   1.0000
  11.250   1.6097   0.02410   0.01796  -0.0946   0.2547   1.0000
  11.500   1.6221   0.02506   0.01892  -0.0931   0.2429   1.0000
  11.750   1.6315   0.02624   0.02006  -0.0914   0.2298   1.0000
  12.000   1.6387   0.02759   0.02136  -0.0895   0.2153   1.0000
  12.250   1.6444   0.02909   0.02280  -0.0875   0.2001   1.0000
  12.500   1.6468   0.03088   0.02451  -0.0853   0.1834   1.0000
  12.750   1.6461   0.03298   0.02651  -0.0831   0.1649   1.0000
  13.000   1.6441   0.03526   0.02870  -0.0808   0.1451   1.0000
  13.250   1.6378   0.03799   0.03130  -0.0784   0.1224   1.0000
  13.500   1.6246   0.04147   0.03461  -0.0759   0.0960   1.0000
  13.750   1.6111   0.04515   0.03818  -0.0736   0.0763   1.0000
  14.000   1.6005   0.04872   0.04170  -0.0718   0.0605   1.0000
  14.250   1.5930   0.05215   0.04510  -0.0704   0.0507   1.0000
  14.500   1.5888   0.05534   0.04832  -0.0693   0.0466   1.0000
  14.750   1.5862   0.05843   0.05146  -0.0685   0.0444   1.0000
  15.000   1.5821   0.06179   0.05488  -0.0677   0.0428   1.0000
  15.250   1.5793   0.06509   0.05826  -0.0672   0.0417   1.0000
  15.500   1.5767   0.06843   0.06170  -0.0668   0.0409   1.0000
  15.750   1.5723   0.07203   0.06539  -0.0665   0.0401   1.0000
  16.000   1.5663   0.07592   0.06937  -0.0663   0.0394   1.0000
  16.250   1.5585   0.08012   0.07367  -0.0663   0.0388   1.0000
  16.500   1.5490   0.08464   0.07829  -0.0665   0.0382   1.0000
  16.750   1.5380   0.08943   0.08317  -0.0669   0.0377   1.0000
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