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GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 419 AIRFOIL (goe419-il)
Reynolds number: 50,000
Max Cl/Cd: 42.32 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe419-il-50000.txt
Download as CSV file: xf-goe419-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 419 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3845   0.10557   0.09887  -0.0223   1.0000   0.1156
  -8.000  -0.3925   0.10482   0.09826  -0.0231   1.0000   0.1180
  -7.750  -0.4003   0.10456   0.09814  -0.0262   1.0000   0.1189
  -7.500  -0.3834   0.09760   0.09117  -0.0219   1.0000   0.1251
  -7.250  -0.3839   0.09557   0.08924  -0.0232   1.0000   0.1301
  -7.000  -0.3874   0.09533   0.08910  -0.0285   1.0000   0.1324
  -6.750  -0.3767   0.08927   0.08310  -0.0235   1.0000   0.1392
  -6.500  -0.3757   0.08804   0.08195  -0.0275   1.0000   0.1452
  -6.000  -0.3646   0.08216   0.07616  -0.0291   1.0000   0.1588
  -5.750  -0.3592   0.07775   0.07174  -0.0259   1.0000   0.1656
  -5.500  -0.3527   0.07522   0.06924  -0.0282   1.0000   0.1747
  -5.250  -0.3441   0.07288   0.06689  -0.0303   1.0000   0.1868
  -5.000  -0.3358   0.07001   0.06402  -0.0305   1.0000   0.2000
  -4.750  -0.3286   0.06669   0.06074  -0.0295   1.0000   0.2138
  -4.500  -0.3221   0.06328   0.05739  -0.0276   1.0000   0.2290
  -4.250  -0.3107   0.06081   0.05486  -0.0286   1.0000   0.2537
  -4.000  -0.3057   0.05739   0.05153  -0.0253   1.0000   0.2746
  -3.750  -0.3006   0.05450   0.04870  -0.0228   1.0000   0.3126
  -3.000  -0.3105   0.04630   0.04091  -0.0041   1.0000   0.4868
  -2.750  -0.3096   0.04362   0.03834   0.0012   1.0000   0.5377
  -2.500  -0.3034   0.04087   0.03564   0.0051   1.0000   0.5781
  -2.250  -0.2870   0.03798   0.03276   0.0057   1.0000   0.6057
  -2.000  -0.0617   0.03352   0.02472  -0.0470   1.0000   0.1574
  -1.750  -0.0340   0.03143   0.02222  -0.0472   1.0000   0.1566
  -1.500  -0.0062   0.02953   0.01986  -0.0472   1.0000   0.1557
  -1.250   0.0217   0.02777   0.01761  -0.0469   1.0000   0.1517
  -1.000   0.0477   0.02641   0.01581  -0.0464   1.0000   0.1545
  -0.750   0.0702   0.02557   0.01468  -0.0457   1.0000   0.1739
  -0.500   0.0967   0.02473   0.01353  -0.0454   1.0000   0.1875
  -0.250   0.1232   0.02402   0.01266  -0.0452   1.0000   0.2061
   0.000   0.1480   0.02337   0.01204  -0.0449   1.0000   0.2459
   0.250   0.1801   0.02050   0.01079  -0.0454   1.0000   1.0000
   0.500   0.1983   0.02111   0.01090  -0.0446   1.0000   1.0000
   0.750   0.2158   0.02176   0.01126  -0.0441   1.0000   1.0000
   1.000   0.2328   0.02247   0.01174  -0.0436   1.0000   1.0000
   1.250   0.2495   0.02324   0.01234  -0.0432   1.0000   1.0000
   1.500   0.2886   0.02436   0.01329  -0.0473   0.9891   1.0000
   1.750   0.3404   0.02556   0.01435  -0.0534   0.9721   1.0000
   2.000   0.3887   0.02655   0.01528  -0.0587   0.9548   1.0000
   2.250   0.4337   0.02740   0.01612  -0.0632   0.9363   1.0000
   2.500   0.4838   0.02820   0.01699  -0.0683   0.9190   1.0000
   2.750   0.5232   0.02892   0.01788  -0.0713   0.8995   1.0000
   3.000   0.5683   0.02956   0.01867  -0.0751   0.8810   1.0000
   3.250   0.6112   0.03015   0.01947  -0.0782   0.8627   1.0000
   3.500   0.6474   0.03077   0.02033  -0.0801   0.8431   1.0000
   3.750   0.6944   0.03111   0.02101  -0.0833   0.8259   1.0000
   4.000   0.7266   0.03173   0.02211  -0.0841   0.8067   1.0000
   4.250   0.8416   0.02128   0.01235  -0.0782   0.6844   1.0000
   4.500   0.8613   0.02035   0.01130  -0.0722   0.6036   1.0000
   4.750   0.8662   0.02069   0.01085  -0.0653   0.4456   1.0000
   5.000   0.8593   0.02413   0.01190  -0.0601   0.1247   1.0000
   5.250   0.8726   0.02641   0.01401  -0.0578   0.0936   1.0000
   5.500   0.8888   0.02804   0.01580  -0.0556   0.0852   1.0000
   5.750   0.9020   0.02993   0.01779  -0.0531   0.0810   1.0000
   6.000   0.9202   0.03162   0.01968  -0.0508   0.0788   1.0000
   6.250   0.9484   0.03360   0.02180  -0.0495   0.0780   1.0000
   6.500   0.9921   0.03635   0.02466  -0.0500   0.0780   1.0000
   6.750   1.0285   0.03931   0.02789  -0.0499   0.0766   1.0000
   7.000   1.0578   0.04250   0.03148  -0.0491   0.0758   1.0000
   7.250   1.0860   0.04653   0.03584  -0.0483   0.0792   1.0000
   7.500   1.1059   0.04971   0.03977  -0.0459   0.0844   1.0000
   7.750   1.1223   0.05422   0.04483  -0.0438   0.0909   1.0000
   8.000   1.1309   0.05804   0.04959  -0.0409   0.0983   1.0000
   8.250   1.1450   0.06345   0.05536  -0.0393   0.1074   1.0000
   8.500   1.1319   0.06765   0.06035  -0.0359   0.1149   1.0000
   9.000   1.1182   0.07827   0.07175  -0.0327   0.1339   1.0000
   9.250   1.0897   0.08255   0.07629  -0.0312   0.1353   1.0000
   9.500   1.0620   0.08686   0.08055  -0.0301   0.1360   1.0000
   9.750   1.0338   0.09200   0.08575  -0.0311   0.1362   1.0000
  10.000   1.0071   0.09822   0.09198  -0.0343   0.1361   1.0000
  10.250   0.9802   0.10623   0.09995  -0.0401   0.1368   1.0000
  10.500   0.9630   0.11574   0.10941  -0.0467   0.1479   1.0000
  10.750   0.9396   0.12542   0.11898  -0.0543   0.1629   1.0000
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