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GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 358 AIRFOIL (goe358-il)
Reynolds number: 50,000
Max Cl/Cd: 37.5 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe358-il-50000.txt
Download as CSV file: xf-goe358-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 358 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3137   0.12068   0.11327  -0.0271   1.0000   0.2162
  -9.000  -0.2982   0.11644   0.10901  -0.0262   1.0000   0.2234
  -8.750  -0.3122   0.11693   0.10965  -0.0265   1.0000   0.2292
  -8.500  -0.2963   0.11183   0.10454  -0.0257   1.0000   0.2339
  -8.250  -0.2957   0.11011   0.10289  -0.0250   1.0000   0.2426
  -8.000  -0.3049   0.10894   0.10185  -0.0244   1.0000   0.2467
  -7.750  -0.2891   0.10494   0.09785  -0.0231   1.0000   0.2557
  -7.500  -0.3152   0.10653   0.09963  -0.0214   1.0000   0.2604
  -7.250  -0.2919   0.10075   0.09383  -0.0206   1.0000   0.2664
  -7.000  -0.2997   0.09978   0.09297  -0.0186   1.0000   0.2737
  -6.750  -0.3352   0.10207   0.09550  -0.0160   1.0000   0.2765
  -6.500  -0.3032   0.09554   0.08889  -0.0145   1.0000   0.2861
  -6.250  -0.3296   0.09663   0.09018  -0.0123   1.0000   0.2917
  -6.000  -0.3185   0.09248   0.08605  -0.0100   1.0000   0.2975
  -5.750  -0.3249   0.09127   0.08494  -0.0083   1.0000   0.3055
  -5.500  -0.3380   0.09039   0.08420  -0.0080   1.0000   0.3100
  -5.250  -0.3299   0.08701   0.08085  -0.0051   1.0000   0.3152
  -5.000  -0.3416   0.08705   0.08099  -0.0067   1.0000   0.3244
  -4.750  -0.3370   0.08351   0.07751  -0.0037   1.0000   0.3287
  -4.500  -0.3360   0.08178   0.07582  -0.0030   1.0000   0.3383
  -4.250  -0.3349   0.07960   0.07369  -0.0042   1.0000   0.3439
  -4.000  -0.3296   0.07701   0.07114  -0.0026   1.0000   0.3489
  -3.500  -0.1623   0.04672   0.03951  -0.0752   1.0000   0.2010
  -3.250  -0.1263   0.04347   0.03603  -0.0804   1.0000   0.2041
  -3.000  -0.0668   0.03785   0.02979  -0.0922   1.0000   0.2088
  -2.750  -0.0162   0.03413   0.02544  -0.1001   1.0000   0.2173
  -2.500   0.0173   0.03287   0.02388  -0.1029   1.0000   0.2302
  -2.250   0.0383   0.03289   0.02400  -0.1025   1.0000   0.2402
  -2.000   0.0656   0.03245   0.02348  -0.1037   1.0000   0.2559
  -1.750   0.0886   0.03267   0.02371  -0.1038   1.0000   0.2793
  -1.500   0.1071   0.03339   0.02454  -0.1029   1.0000   0.3108
  -1.250   0.1216   0.03435   0.02569  -0.1010   1.0000   0.3484
  -1.000   0.1644   0.03547   0.02689  -0.1034   0.9883   0.4138
  -0.750   0.2136   0.03613   0.02757  -0.1068   0.9726   0.4746
  -0.500   0.2595   0.03635   0.02783  -0.1097   0.9570   0.5340
  -0.250   0.3101   0.03598   0.02738  -0.1142   0.9414   0.5679
   0.000   0.3571   0.03566   0.02696  -0.1183   0.9241   0.5916
   0.250   0.4039   0.03543   0.02661  -0.1224   0.9060   0.6134
   0.500   0.4476   0.03510   0.02622  -0.1254   0.8881   0.6331
   0.750   0.4920   0.03480   0.02584  -0.1285   0.8704   0.6513
   1.000   0.5373   0.03445   0.02542  -0.1317   0.8531   0.6670
   1.250   0.5833   0.03406   0.02497  -0.1347   0.8364   0.6813
   1.500   0.6290   0.03364   0.02450  -0.1375   0.8203   0.6959
   1.750   0.6724   0.03318   0.02403  -0.1397   0.8045   0.7105
   2.000   0.7122   0.03276   0.02362  -0.1411   0.7890   0.7267
   2.250   0.7495   0.03242   0.02334  -0.1421   0.7738   0.7442
   2.500   0.7844   0.03217   0.02319  -0.1427   0.7595   0.7656
   2.750   0.8196   0.03170   0.02292  -0.1431   0.7468   0.7978
   3.000   0.8527   0.03120   0.02265  -0.1429   0.7344   1.0000
   3.250   0.8852   0.03197   0.02336  -0.1443   0.7194   1.0000
   3.500   0.9131   0.03308   0.02439  -0.1451   0.7054   1.0000
   3.750   0.9401   0.03430   0.02556  -0.1458   0.6933   1.0000
   4.000   0.9802   0.03447   0.02564  -0.1472   0.6848   1.0000
   4.250   0.9950   0.03646   0.02763  -0.1467   0.6718   1.0000
   4.500   1.0152   0.03811   0.02927  -0.1465   0.6617   1.0000
   4.750   1.0412   0.03930   0.03046  -0.1467   0.6535   1.0000
   5.000   1.0477   0.04212   0.03332  -0.1457   0.6430   1.0000
   5.250   1.0868   0.04190   0.03312  -0.1459   0.6355   1.0000
   5.500   1.0847   0.04531   0.03660  -0.1443   0.6236   1.0000
   5.750   1.1029   0.04678   0.03812  -0.1432   0.6133   1.0000
   6.000   1.1492   0.04531   0.03670  -0.1428   0.6031   1.0000
   6.250   1.1504   0.04814   0.03963  -0.1408   0.5902   1.0000
   6.500   1.1574   0.05057   0.04216  -0.1392   0.5790   1.0000
   6.750   1.2070   0.04896   0.04067  -0.1389   0.5707   1.0000
   7.000   1.1853   0.05429   0.04612  -0.1366   0.5585   1.0000
   7.250   1.1875   0.05725   0.04919  -0.1349   0.5471   1.0000
   7.500   1.2587   0.05297   0.04510  -0.1342   0.5359   1.0000
   7.750   1.2903   0.05191   0.04420  -0.1319   0.5184   1.0000
   8.000   1.3716   0.04413   0.03632  -0.1298   0.4873   1.0000
   8.250   1.3898   0.04396   0.03632  -0.1269   0.4644   1.0000
   8.500   1.4304   0.04167   0.03395  -0.1250   0.4379   1.0000
   8.750   1.4577   0.04031   0.03252  -0.1223   0.4068   1.0000
   9.000   1.4688   0.03997   0.03224  -0.1181   0.3708   1.0000
   9.250   1.4779   0.03941   0.03141  -0.1133   0.3254   1.0000
   9.500   1.4733   0.04018   0.03200  -0.1077   0.2816   1.0000
   9.750   1.4671   0.04149   0.03309  -0.1025   0.2462   1.0000
  10.000   1.4647   0.04306   0.03432  -0.0982   0.2197   1.0000
  10.250   1.4634   0.04516   0.03628  -0.0943   0.1988   1.0000
  10.500   1.4800   0.04755   0.03811  -0.0926   0.1778   1.0000
  10.750   1.4989   0.05065   0.04117  -0.0914   0.1612   1.0000
  11.000   1.5244   0.05405   0.04447  -0.0911   0.1471   1.0000
  11.250   1.5258   0.05702   0.04784  -0.0881   0.1402   1.0000
  11.500   1.5482   0.06071   0.05153  -0.0877   0.1319   1.0000
  11.750   1.5389   0.06383   0.05509  -0.0839   0.1285   1.0000
  12.000   1.5413   0.06707   0.05854  -0.0816   0.1238   1.0000
  12.250   1.5598   0.07140   0.06291  -0.0812   0.1191   1.0000
  12.500   1.5391   0.07507   0.06697  -0.0773   0.1184   1.0000
  12.750   1.5160   0.07924   0.07150  -0.0742   0.1179   1.0000
  13.000   1.4903   0.08400   0.07658  -0.0722   0.1177   1.0000
  13.250   1.4625   0.08946   0.08234  -0.0712   0.1178   1.0000
  13.500   1.4326   0.09574   0.08888  -0.0715   0.1182   1.0000
  13.750   1.4022   0.10287   0.09621  -0.0731   0.1188   1.0000
  14.000   1.3721   0.11084   0.10436  -0.0757   0.1195   1.0000
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