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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 100,000
Max Cl/Cd: 66.69 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe123-il-100000-n5.txt
Download as CSV file: xf-goe123-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3027   0.10501   0.10028  -0.0282   1.0000   0.0344
  -7.750  -0.3167   0.10501   0.10041  -0.0258   1.0000   0.0345
  -7.500  -0.3270   0.10473   0.10021  -0.0249   1.0000   0.0347
  -7.250  -0.3194   0.10334   0.09884  -0.0302   0.9966   0.0349
  -7.000  -0.3035   0.09765   0.09317  -0.0324   0.9927   0.0353
  -6.750  -0.2923   0.09227   0.08780  -0.0305   0.9901   0.0363
  -6.500  -0.2723   0.08820   0.08370  -0.0339   0.9860   0.0376
  -6.250  -0.2512   0.08456   0.08004  -0.0383   0.9800   0.0392
  -6.000  -0.2259   0.08088   0.07633  -0.0442   0.9747   0.0415
  -5.750  -0.1669   0.07869   0.07389  -0.0637   0.9671   0.0457
  -5.500  -0.1501   0.07378   0.06900  -0.0654   0.9615   0.0463
  -5.250  -0.1352   0.06937   0.06462  -0.0650   0.9582   0.0477
  -5.000  -0.1103   0.06598   0.06118  -0.0684   0.9535   0.0501
  -4.500  -0.0277   0.05914   0.05402  -0.0847   0.9442   0.0583
  -4.250  -0.0104   0.05599   0.05086  -0.0851   0.9377   0.0601
  -4.000   0.0231   0.05294   0.04771  -0.0894   0.9337   0.0637
  -3.750   0.0833   0.05195   0.04620  -0.0992   0.9273   0.0696
  -3.500   0.0972   0.04721   0.04163  -0.0991   0.9221   0.0718
  -3.250   0.1299   0.04447   0.03879  -0.1020   0.9182   0.0762
  -3.000   0.1788   0.04424   0.03803  -0.1071   0.9101   0.0831
  -2.750   0.2079   0.04025   0.03402  -0.1095   0.9058   0.0842
  -2.500   0.2324   0.03768   0.03143  -0.1104   0.8993   0.0859
  -2.250   0.2616   0.03568   0.02932  -0.1118   0.8934   0.0894
  -2.000   0.3016   0.03408   0.02741  -0.1147   0.8895   0.0993
  -1.500   0.3725   0.02850   0.02105  -0.1172   0.8771   0.0560
  -1.250   0.4040   0.02684   0.01920  -0.1182   0.8719   0.0544
  -1.000   0.4330   0.02542   0.01756  -0.1185   0.8644   0.0532
  -0.750   0.4667   0.02388   0.01575  -0.1193   0.8596   0.0522
  -0.500   0.4943   0.02281   0.01444  -0.1190   0.8503   0.0536
  -0.250   0.5259   0.02160   0.01293  -0.1190   0.8426   0.0553
   0.000   0.5538   0.02055   0.01167  -0.1185   0.8318   0.0551
   0.250   0.5812   0.01962   0.01056  -0.1179   0.8211   0.0549
   0.500   0.6105   0.01872   0.00949  -0.1176   0.8129   0.0551
   0.750   0.6367   0.01810   0.00877  -0.1169   0.8023   0.0555
   1.000   0.6635   0.01754   0.00814  -0.1163   0.7924   0.0563
   1.250   0.6909   0.01698   0.00753  -0.1157   0.7836   0.0574
   1.500   0.7163   0.01663   0.00721  -0.1149   0.7718   0.0596
   1.750   0.7426   0.01640   0.00697  -0.1142   0.7601   0.0648
   2.000   0.7694   0.01618   0.00673  -0.1137   0.7483   0.0727
   2.250   0.7964   0.01597   0.00648  -0.1131   0.7358   0.0826
   2.500   0.8234   0.01580   0.00642  -0.1125   0.7221   0.1129
   2.750   0.8499   0.01567   0.00632  -0.1120   0.7071   0.1725
   3.000   0.8720   0.01427   0.00632  -0.1106   0.6909   1.0000
   3.250   0.8977   0.01438   0.00633  -0.1099   0.6725   1.0000
   3.500   0.9232   0.01449   0.00634  -0.1091   0.6520   1.0000
   3.750   0.9485   0.01463   0.00635  -0.1082   0.6285   1.0000
   4.000   0.9734   0.01480   0.00641  -0.1073   0.6027   1.0000
   4.250   0.9980   0.01504   0.00652  -0.1065   0.5759   1.0000
   4.500   1.0224   0.01533   0.00669  -0.1056   0.5500   1.0000
   5.000   1.0701   0.01609   0.00724  -0.1039   0.5005   1.0000
   5.250   1.0934   0.01654   0.00759  -0.1030   0.4754   1.0000
   5.500   1.1163   0.01701   0.00798  -0.1021   0.4509   1.0000
   5.750   1.1391   0.01750   0.00842  -0.1012   0.4275   1.0000
   6.000   1.1615   0.01801   0.00891  -0.1003   0.4060   1.0000
   6.250   1.1840   0.01854   0.00941  -0.0994   0.3876   1.0000
   6.500   1.2065   0.01907   0.00996  -0.0986   0.3702   1.0000
   6.750   1.2283   0.01964   0.01054  -0.0977   0.3514   1.0000
   7.000   1.2493   0.02024   0.01118  -0.0966   0.3317   1.0000
   7.250   1.2695   0.02090   0.01181  -0.0955   0.3120   1.0000
   7.500   1.2893   0.02153   0.01249  -0.0944   0.2886   1.0000
   7.750   1.3074   0.02225   0.01319  -0.0930   0.2600   1.0000
   8.000   1.3248   0.02304   0.01397  -0.0916   0.2268   1.0000
   8.250   1.3394   0.02407   0.01484  -0.0900   0.1826   1.0000
   8.500   1.3490   0.02568   0.01605  -0.0878   0.1149   1.0000
   8.750   1.3540   0.02784   0.01780  -0.0851   0.0723   1.0000
   9.000   1.3626   0.02959   0.01945  -0.0827   0.0489   1.0000
   9.250   1.3703   0.03125   0.02112  -0.0802   0.0412   1.0000
   9.500   1.3734   0.03303   0.02295  -0.0772   0.0374   1.0000
   9.750   1.3770   0.03475   0.02488  -0.0743   0.0346   1.0000
  10.000   1.3801   0.03654   0.02686  -0.0716   0.0319   1.0000
  10.250   1.3807   0.03859   0.02905  -0.0691   0.0298   1.0000
  10.500   1.3784   0.04096   0.03157  -0.0665   0.0285   1.0000
  10.750   1.3734   0.04371   0.03443  -0.0640   0.0275   1.0000
  11.000   1.3742   0.04610   0.03697  -0.0619   0.0267   1.0000
  11.250   1.3774   0.04837   0.03943  -0.0602   0.0256   1.0000
  11.500   1.3804   0.05074   0.04199  -0.0586   0.0243   1.0000
  11.750   1.3828   0.05324   0.04465  -0.0572   0.0230   1.0000
  12.000   1.3848   0.05587   0.04743  -0.0559   0.0220   1.0000
  12.250   1.3872   0.05861   0.05034  -0.0545   0.0213   1.0000
  12.500   1.3893   0.06147   0.05334  -0.0533   0.0207   1.0000
  12.750   1.3910   0.06450   0.05652  -0.0522   0.0201   1.0000
  13.000   1.3924   0.06777   0.05993  -0.0511   0.0197   1.0000
  13.250   1.3928   0.07157   0.06389  -0.0499   0.0191   1.0000
  13.500   1.3873   0.07557   0.06813  -0.0495   0.0188   1.0000
  13.750   1.3788   0.07979   0.07264  -0.0497   0.0185   1.0000
  14.000   1.3686   0.08441   0.07755  -0.0503   0.0183   1.0000
  14.250   1.3569   0.08946   0.08287  -0.0515   0.0180   1.0000
  14.500   1.3438   0.09494   0.08862  -0.0532   0.0178   1.0000
  14.750   1.3297   0.10093   0.09485  -0.0556   0.0177   1.0000
  15.000   1.3150   0.10743   0.10160  -0.0586   0.0176   1.0000
  15.250   1.2995   0.11448   0.10888  -0.0624   0.0175   1.0000
  15.500   1.2835   0.12205   0.11666  -0.0667   0.0176   1.0000
  15.750   1.2670   0.13024   0.12506  -0.0717   0.0177   1.0000
  16.000   1.2504   0.13903   0.13403  -0.0774   0.0178   1.0000
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