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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.57 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe114-il-1000000-n5.txt
Download as CSV file: xf-goe114-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 114 (MVA MK.1) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2799   0.10949   0.10798  -0.0406   1.0000   0.0021
 -11.000  -0.2786   0.10606   0.10456  -0.0412   1.0000   0.0021
 -10.750  -0.2776   0.10244   0.10096  -0.0417   1.0000   0.0021
 -10.500  -0.2742   0.09835   0.09687  -0.0432   0.9949   0.0021
 -10.250  -0.2694   0.09399   0.09251  -0.0453   0.9913   0.0021
 -10.000  -0.2646   0.08924   0.08777  -0.0477   0.9878   0.0021
  -9.750  -0.2594   0.08458   0.08310  -0.0501   0.9831   0.0021
  -9.500  -0.2538   0.07948   0.07800  -0.0531   0.9790   0.0021
  -9.250  -0.2477   0.07418   0.07270  -0.0563   0.9733   0.0021
  -9.000  -0.2404   0.06858   0.06709  -0.0602   0.9676   0.0021
  -8.750  -0.2327   0.06272   0.06122  -0.0646   0.9593   0.0021
  -8.500  -0.2246   0.05662   0.05509  -0.0694   0.9480   0.0021
  -8.250  -0.2191   0.05045   0.04888  -0.0739   0.9310   0.0021
  -8.000  -0.2193   0.04460   0.04296  -0.0770   0.9088   0.0021
  -7.750  -0.2253   0.03914   0.03739  -0.0798   0.8869   0.0021
  -7.500  -0.2383   0.03403   0.03219  -0.0830   0.8670   0.0021
  -7.250  -0.2514   0.03000   0.02805  -0.0884   0.8497   0.0021
  -7.000  -0.2560   0.02545   0.02326  -0.0937   0.8371   0.0021
  -5.500  -0.1881   0.02137   0.01722  -0.1030   0.8041   0.0016
  -5.250  -0.1659   0.01900   0.01452  -0.1020   0.7969   0.0014
  -5.000  -0.1424   0.01681   0.01200  -0.1008   0.7903   0.0013
  -4.750  -0.1176   0.01498   0.00993  -0.0999   0.7835   0.0013
  -4.500  -0.0923   0.01348   0.00821  -0.0990   0.7772   0.0016
  -4.250  -0.0668   0.01212   0.00672  -0.0982   0.7708   0.0018
  -3.750  -0.0161   0.01065   0.00503  -0.0973   0.7582   0.0029
  -3.500   0.0085   0.00970   0.00396  -0.0966   0.7518   0.0028
  -3.250   0.0339   0.00895   0.00308  -0.0961   0.7459   0.0027
  -3.000   0.0600   0.00841   0.00238  -0.0957   0.7391   0.0030
  -2.750   0.0867   0.00804   0.00186  -0.0955   0.7329   0.0036
  -2.500   0.1138   0.00780   0.00154  -0.0954   0.7266   0.0053
  -2.250   0.1409   0.00763   0.00127  -0.0953   0.7204   0.0087
  -2.000   0.1682   0.00751   0.00110  -0.0952   0.7125   0.0190
  -1.750   0.1911   0.00654   0.00077  -0.0949   0.7032   0.2464
  -1.500   0.2177   0.00648   0.00076  -0.0948   0.6925   0.2833
  -1.250   0.2448   0.00647   0.00074  -0.0947   0.6822   0.2977
  -1.000   0.2722   0.00649   0.00070  -0.0947   0.6744   0.3037
  -0.750   0.2994   0.00650   0.00068  -0.0947   0.6656   0.3074
  -0.500   0.3267   0.00651   0.00067  -0.0947   0.6560   0.3104
  -0.250   0.3538   0.00655   0.00067  -0.0947   0.6464   0.3135
   0.000   0.3809   0.00659   0.00068  -0.0947   0.6365   0.3164
   0.250   0.4079   0.00662   0.00070  -0.0946   0.6252   0.3194
   0.500   0.4349   0.00666   0.00074  -0.0945   0.6135   0.3230
   0.750   0.4591   0.00688   0.00081  -0.0940   0.5715   0.3266
   1.000   0.4831   0.00715   0.00090  -0.0934   0.5267   0.3298
   1.250   0.5037   0.00770   0.00110  -0.0922   0.4401   0.3333
   1.500   0.5077   0.00985   0.00189  -0.0884   0.1012   0.3357
   1.750   0.5310   0.01027   0.00215  -0.0877   0.0122   0.3392
   2.000   0.5567   0.01046   0.00243  -0.0873   0.0070   0.3434
   2.250   0.5824   0.01062   0.00262  -0.0870   0.0045   0.3473
   2.500   0.6067   0.01095   0.00305  -0.0863   0.0034   0.3512
   2.750   0.6300   0.01139   0.00360  -0.0854   0.0031   0.3550
   3.000   0.6518   0.01197   0.00429  -0.0842   0.0030   0.3586
   3.250   0.6737   0.01245   0.00482  -0.0832   0.0022   0.3622
   3.500   0.6955   0.01297   0.00544  -0.0820   0.0017   0.3660
   3.750   0.7132   0.01388   0.00646  -0.0799   0.0014   0.3698
   4.000   0.7307   0.01493   0.00758  -0.0778   0.0013   0.3732
   4.250   0.7504   0.01618   0.00890  -0.0759   0.0013   0.3774
   4.500   0.7756   0.01787   0.01065  -0.0748   0.0014   0.3821
   4.750   0.8048   0.01975   0.01262  -0.0744   0.0018   0.3871
   7.750   1.0326   0.04799   0.04461  -0.0539   0.0021   1.0000
   8.000   1.0450   0.05072   0.04757  -0.0510   0.0019   1.0000
   8.250   1.0497   0.05388   0.05092  -0.0480   0.0019   1.0000
   8.500   1.0518   0.05707   0.05429  -0.0450   0.0018   1.0000
   8.750   1.0505   0.06037   0.05776  -0.0419   0.0017   1.0000
   9.000   1.0452   0.06349   0.06104  -0.0388   0.0018   1.0000
   9.250   1.0362   0.06650   0.06418  -0.0353   0.0017   1.0000
   9.500   1.0201   0.06905   0.06685  -0.0312   0.0018   1.0000
   9.750   1.0027   0.07190   0.06981  -0.0282   0.0018   1.0000
  10.000   0.9842   0.07522   0.07323  -0.0263   0.0018   1.0000
  10.250   0.9642   0.07907   0.07718  -0.0255   0.0018   1.0000
  10.500   0.9453   0.08341   0.08162  -0.0259   0.0018   1.0000
  10.750   0.9256   0.08841   0.08672  -0.0274   0.0018   1.0000
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