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GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 391 AIRFOIL (goe391-il)
Reynolds number: 100,000
Max Cl/Cd: 58.75 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe391-il-100000.txt
Download as CSV file: xf-goe391-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 391 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4325   0.09769   0.09268  -0.0217   1.0000   0.0483
  -7.750  -0.4383   0.09603   0.09112  -0.0226   1.0000   0.0489
  -7.500  -0.4395   0.09418   0.08934  -0.0259   1.0000   0.0494
  -7.250  -0.3651   0.07705   0.07258  -0.0237   1.0000   0.0532
  -7.000  -0.3691   0.07427   0.06986  -0.0226   1.0000   0.0542
  -6.750  -0.3719   0.07134   0.06698  -0.0222   1.0000   0.0556
  -6.500  -0.3743   0.06837   0.06406  -0.0222   1.0000   0.0570
  -6.250  -0.3757   0.06537   0.06109  -0.0226   1.0000   0.0587
  -6.000  -0.3754   0.06237   0.05809  -0.0238   1.0000   0.0606
  -5.750  -0.3700   0.06007   0.05570  -0.0280   1.0000   0.0628
  -5.500  -0.3591   0.05853   0.05388  -0.0321   1.0000   0.0637
  -5.250  -0.3714   0.06635   0.06118  -0.0353   1.0000   0.0639
  -5.000  -0.3733   0.06079   0.05591  -0.0314   1.0000   0.0663
  -4.750  -0.3637   0.05795   0.05302  -0.0304   1.0000   0.0719
  -4.500  -0.3398   0.05514   0.04987  -0.0338   1.0000   0.0786
  -4.250  -0.3331   0.05162   0.04648  -0.0317   1.0000   0.0831
  -4.000  -0.3085   0.04921   0.04367  -0.0337   1.0000   0.0923
  -3.750  -0.2982   0.04579   0.04037  -0.0322   1.0000   0.0978
  -3.500  -0.2785   0.04298   0.03735  -0.0326   1.0000   0.1085
  -3.250  -0.2593   0.04043   0.03462  -0.0326   1.0000   0.1216
  -3.000  -0.2414   0.03792   0.03201  -0.0321   1.0000   0.1371
  -2.750  -0.2225   0.03568   0.02958  -0.0319   1.0000   0.1630
  -2.500  -0.2074   0.03362   0.02751  -0.0309   1.0000   0.2045
  -1.250  -0.0582   0.02343   0.01502  -0.0288   1.0000   0.1154
  -1.000  -0.0306   0.02188   0.01304  -0.0277   1.0000   0.1002
  -0.750  -0.0044   0.02088   0.01153  -0.0264   1.0000   0.0922
  -0.500   0.0198   0.01979   0.01031  -0.0255   1.0000   0.0932
  -0.250   0.0427   0.01903   0.00956  -0.0247   1.0000   0.0994
   0.000   0.0658   0.01842   0.00888  -0.0238   1.0000   0.0996
   0.250   0.0881   0.01795   0.00839  -0.0228   1.0000   0.1020
   0.500   0.1105   0.01754   0.00801  -0.0219   1.0000   0.1062
   0.750   0.1310   0.01735   0.00784  -0.0210   1.0000   0.1172
   1.000   0.1535   0.01726   0.00775  -0.0204   1.0000   0.1303
   1.250   0.1774   0.01715   0.00780  -0.0202   1.0000   0.1670
   1.500   0.2342   0.01565   0.00799  -0.0263   0.9953   1.0000
   1.750   0.2891   0.01632   0.00852  -0.0324   0.9830   1.0000
   2.000   0.3409   0.01679   0.00893  -0.0377   0.9700   1.0000
   2.250   0.3868   0.01711   0.00927  -0.0418   0.9573   1.0000
   2.500   0.4350   0.01730   0.00955  -0.0460   0.9437   1.0000
   2.750   0.4862   0.01730   0.00965  -0.0505   0.9293   1.0000
   3.000   0.5329   0.01710   0.00960  -0.0538   0.9122   1.0000
   3.250   0.6079   0.01564   0.00844  -0.0605   0.8866   1.0000
   3.500   0.6539   0.01480   0.00782  -0.0623   0.8630   1.0000
   3.750   0.6920   0.01416   0.00739  -0.0627   0.8366   1.0000
   4.000   0.7266   0.01338   0.00674  -0.0617   0.7864   1.0000
   4.250   0.7591   0.01292   0.00602  -0.0598   0.6633   1.0000
   4.500   0.7784   0.01370   0.00606  -0.0567   0.5066   1.0000
   4.750   0.7809   0.01591   0.00674  -0.0519   0.2401   1.0000
   5.000   0.7906   0.01823   0.00807  -0.0487   0.1208   1.0000
   5.250   0.8083   0.01950   0.00920  -0.0467   0.1044   1.0000
   5.500   0.8271   0.02074   0.01037  -0.0450   0.0918   1.0000
   5.750   0.8489   0.02209   0.01185  -0.0436   0.0850   1.0000
   6.000   0.8727   0.02420   0.01382  -0.0428   0.0777   1.0000
   6.250   0.8977   0.02572   0.01556  -0.0418   0.0704   1.0000
   6.500   0.9254   0.02861   0.01847  -0.0415   0.0663   1.0000
   6.750   0.9487   0.03097   0.02130  -0.0401   0.0622   1.0000
   7.000   0.9704   0.03361   0.02441  -0.0384   0.0595   1.0000
   7.250   0.9896   0.03721   0.02862  -0.0363   0.0601   1.0000
   7.500   1.0049   0.04149   0.03343  -0.0340   0.0624   1.0000
   7.750   1.0176   0.04634   0.03865  -0.0320   0.0643   1.0000
   8.000   1.0299   0.05217   0.04473  -0.0305   0.0655   1.0000
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