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GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 615 AIRFOIL (goe615-il)
Reynolds number: 200,000
Max Cl/Cd: 72.15 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe615-il-200000-n5.txt
Download as CSV file: xf-goe615-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1511   0.09049   0.08675  -0.0738   0.9495   0.0365
  -9.500  -0.1514   0.08229   0.07852  -0.0829   0.9420   0.0374
  -9.250  -0.1390   0.07739   0.07360  -0.0881   0.9335   0.0373
  -9.000  -0.1261   0.07190   0.06807  -0.0946   0.9256   0.0373
  -8.750  -0.1204   0.06506   0.06118  -0.1027   0.9137   0.0373
  -8.500  -0.1075   0.06147   0.05758  -0.1074   0.9020   0.0379
  -8.000  -0.1533   0.03919   0.03452  -0.1258   0.8670   0.0381
  -7.750  -0.1430   0.03614   0.03119  -0.1265   0.8580   0.0384
  -7.500  -0.1343   0.03353   0.02830  -0.1258   0.8476   0.0387
  -7.250  -0.1208   0.03097   0.02539  -0.1254   0.8394   0.0391
  -7.000  -0.1057   0.02915   0.02331  -0.1245   0.8300   0.0397
  -6.750  -0.0873   0.02731   0.02113  -0.1238   0.8223   0.0406
  -6.500  -0.0705   0.02557   0.01903  -0.1226   0.8129   0.0414
  -6.250  -0.0497   0.02396   0.01703  -0.1218   0.8051   0.0419
  -6.000  -0.0296   0.02267   0.01541  -0.1206   0.7957   0.0424
  -5.750  -0.0061   0.02155   0.01394  -0.1199   0.7880   0.0429
  -5.500   0.0163   0.02059   0.01281  -0.1190   0.7789   0.0434
  -5.000   0.0653   0.01927   0.01132  -0.1178   0.7618   0.0449
  -4.750   0.0911   0.01870   0.01061  -0.1173   0.7538   0.0459
  -4.500   0.1152   0.01814   0.00994  -0.1165   0.7442   0.0468
  -4.250   0.1410   0.01756   0.00920  -0.1159   0.7356   0.0476
  -4.000   0.1657   0.01705   0.00857  -0.1151   0.7254   0.0484
  -3.750   0.1913   0.01661   0.00799  -0.1144   0.7160   0.0492
  -3.500   0.2161   0.01611   0.00744  -0.1137   0.7059   0.0501
  -3.250   0.2409   0.01569   0.00701  -0.1130   0.6966   0.0513
  -3.000   0.2661   0.01538   0.00666  -0.1123   0.6871   0.0529
  -2.750   0.2911   0.01509   0.00633  -0.1116   0.6777   0.0546
  -2.500   0.3165   0.01483   0.00598  -0.1110   0.6688   0.0561
  -2.250   0.3413   0.01460   0.00570  -0.1102   0.6591   0.0574
  -2.000   0.3656   0.01431   0.00537  -0.1094   0.6491   0.0592
  -1.750   0.3900   0.01413   0.00515  -0.1086   0.6379   0.0617
  -1.500   0.4149   0.01400   0.00495  -0.1078   0.6276   0.0648
  -1.250   0.4396   0.01386   0.00474  -0.1070   0.6180   0.0686
  -1.000   0.4645   0.01375   0.00461  -0.1063   0.6085   0.0730
  -0.750   0.4895   0.01366   0.00447  -0.1056   0.5998   0.0801
  -0.500   0.5139   0.01353   0.00438  -0.1048   0.5905   0.0980
  -0.250   0.5373   0.01324   0.00434  -0.1040   0.5827   0.1788
   0.000   0.5613   0.01307   0.00438  -0.1032   0.5752   0.2530
   0.250   0.5852   0.01295   0.00441  -0.1024   0.5685   0.3184
   0.500   0.6081   0.01273   0.00448  -0.1015   0.5623   0.4150
   0.750   0.6277   0.01233   0.00459  -0.0998   0.5561   0.5759
   1.250   0.7404   0.01191   0.00483  -0.1112   0.5409   1.0000
   1.500   0.7634   0.01207   0.00489  -0.1101   0.5345   1.0000
   1.750   0.7865   0.01224   0.00496  -0.1091   0.5284   1.0000
   2.000   0.8095   0.01238   0.00505  -0.1080   0.5218   1.0000
   2.250   0.8323   0.01257   0.00514  -0.1069   0.5151   1.0000
   2.500   0.8551   0.01272   0.00525  -0.1059   0.5083   1.0000
   2.750   0.8776   0.01289   0.00537  -0.1047   0.5011   1.0000
   3.000   0.9001   0.01308   0.00548  -0.1036   0.4941   1.0000
   3.250   0.9222   0.01323   0.00563  -0.1024   0.4858   1.0000
   3.500   0.9440   0.01343   0.00574  -0.1012   0.4780   1.0000
   3.750   0.9651   0.01358   0.00590  -0.0999   0.4677   1.0000
   4.000   0.9854   0.01377   0.00604  -0.0984   0.4563   1.0000
   4.250   1.0046   0.01397   0.00618  -0.0967   0.4426   1.0000
   4.500   1.0231   0.01418   0.00634  -0.0949   0.4266   1.0000
   4.750   1.0404   0.01443   0.00651  -0.0929   0.4072   1.0000
   5.000   1.0555   0.01475   0.00671  -0.0905   0.3859   1.0000
   5.250   1.0688   0.01513   0.00696  -0.0879   0.3667   1.0000
   5.500   1.0815   0.01554   0.00725  -0.0851   0.3512   1.0000
   5.750   1.0945   0.01594   0.00758  -0.0825   0.3389   1.0000
   6.000   1.1077   0.01637   0.00794  -0.0800   0.3291   1.0000
   6.250   1.1221   0.01681   0.00832  -0.0777   0.3195   1.0000
   6.500   1.1365   0.01726   0.00873  -0.0755   0.3111   1.0000
   6.750   1.1512   0.01773   0.00917  -0.0734   0.3028   1.0000
   7.000   1.1653   0.01823   0.00963  -0.0713   0.2943   1.0000
   7.250   1.1796   0.01874   0.01011  -0.0693   0.2855   1.0000
   7.500   1.1940   0.01927   0.01063  -0.0674   0.2782   1.0000
   7.750   1.2096   0.01977   0.01114  -0.0657   0.2713   1.0000
   8.250   1.2384   0.02091   0.01227  -0.0622   0.2579   1.0000
   8.500   1.2520   0.02154   0.01291  -0.0604   0.2514   1.0000
   8.750   1.2657   0.02218   0.01356  -0.0587   0.2456   1.0000
   9.000   1.2805   0.02280   0.01421  -0.0572   0.2398   1.0000
   9.250   1.2932   0.02354   0.01497  -0.0556   0.2344   1.0000
   9.500   1.3067   0.02426   0.01572  -0.0541   0.2295   1.0000
   9.750   1.3205   0.02499   0.01650  -0.0527   0.2239   1.0000
  10.000   1.3322   0.02585   0.01738  -0.0511   0.2188   1.0000
  10.250   1.3441   0.02673   0.01829  -0.0496   0.2129   1.0000
  10.500   1.3559   0.02764   0.01926  -0.0482   0.2069   1.0000
  10.750   1.3652   0.02874   0.02037  -0.0467   0.2016   1.0000
  11.000   1.3774   0.02969   0.02138  -0.0455   0.1961   1.0000
  11.250   1.3866   0.03086   0.02259  -0.0441   0.1897   1.0000
  11.500   1.3955   0.03208   0.02386  -0.0429   0.1843   1.0000
  11.750   1.4058   0.03325   0.02510  -0.0417   0.1789   1.0000
  12.000   1.4113   0.03481   0.02667  -0.0404   0.1721   1.0000
  12.250   1.4194   0.03621   0.02813  -0.0393   0.1643   1.0000
  12.500   1.4230   0.03803   0.02996  -0.0382   0.1553   1.0000
  12.750   1.4240   0.04014   0.03207  -0.0370   0.1430   1.0000
  13.000   1.4242   0.04241   0.03433  -0.0360   0.1308   1.0000
  13.250   1.4199   0.04521   0.03707  -0.0350   0.1138   1.0000
  13.500   1.4106   0.04863   0.04040  -0.0342   0.0954   1.0000
  13.750   1.4046   0.05185   0.04359  -0.0336   0.0846   1.0000
  14.000   1.3986   0.05520   0.04694  -0.0332   0.0775   1.0000
  14.250   1.3939   0.05853   0.05030  -0.0330   0.0733   1.0000
  14.500   1.3924   0.06158   0.05343  -0.0329   0.0713   1.0000
  14.750   1.3883   0.06500   0.05692  -0.0330   0.0691   1.0000
  15.000   1.3836   0.06859   0.06059  -0.0333   0.0673   1.0000
  15.250   1.3803   0.07211   0.06420  -0.0336   0.0660   1.0000
  15.500   1.3781   0.07551   0.06771  -0.0340   0.0651   1.0000
  15.750   1.3747   0.07914   0.07146  -0.0345   0.0640   1.0000
  16.000   1.3703   0.08296   0.07539  -0.0352   0.0631   1.0000
  16.250   1.3655   0.08693   0.07948  -0.0360   0.0624   1.0000
  16.500   1.3583   0.09130   0.08396  -0.0370   0.0612   1.0000
  16.750   1.3520   0.09561   0.08838  -0.0381   0.0606   1.0000
  17.000   1.3432   0.10038   0.09326  -0.0394   0.0596   1.0000
  17.250   1.3350   0.10516   0.09813  -0.0409   0.0588   1.0000
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