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GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 480 AIRFOIL (goe480-il)
Reynolds number: 100,000
Max Cl/Cd: 57.33 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe480-il-100000-n5.txt
Download as CSV file: xf-goe480-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 480 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2700   0.12422   0.11892  -0.0452   1.0000   0.0707
 -10.750  -0.2841   0.12308   0.11787  -0.0466   1.0000   0.0711
 -10.500  -0.2927   0.12126   0.11614  -0.0468   1.0000   0.0713
 -10.250  -0.2893   0.11759   0.11254  -0.0451   1.0000   0.0717
 -10.000  -0.2730   0.11401   0.10897  -0.0419   1.0000   0.0730
  -9.750  -0.2662   0.11182   0.10683  -0.0405   0.9991   0.0747
  -9.500  -0.2464   0.10829   0.10328  -0.0442   0.9929   0.0786
  -9.250  -0.2384   0.10505   0.10003  -0.0519   0.9838   0.0831
  -9.000  -0.2362   0.10168   0.09666  -0.0614   0.9711   0.0840
  -8.500  -0.1885   0.09308   0.08802  -0.0627   0.9618   0.0871
  -8.250  -0.1695   0.09001   0.08493  -0.0651   0.9535   0.0899
  -8.000  -0.1524   0.08658   0.08148  -0.0696   0.9455   0.0930
  -7.750  -0.1571   0.08292   0.07778  -0.0832   0.9253   0.0976
  -7.500  -0.1404   0.07826   0.07309  -0.0877   0.9173   0.0985
  -7.250  -0.1165   0.07586   0.07070  -0.0839   0.9119   0.1006
  -7.000  -0.0943   0.07289   0.06769  -0.0863   0.9050   0.1031
  -6.750  -0.0894   0.06540   0.06001  -0.0965   0.8904   0.0817
  -6.500  -0.0740   0.06184   0.05637  -0.0996   0.8808   0.0803
  -6.250  -0.0568   0.05779   0.05219  -0.1041   0.8719   0.0798
  -6.000  -0.0427   0.05383   0.04809  -0.1074   0.8619   0.0779
  -5.750  -0.0254   0.04823   0.04219  -0.1125   0.8536   0.0752
  -5.500  -0.0102   0.04392   0.03759  -0.1151   0.8442   0.0746
  -5.250   0.0114   0.04118   0.03464  -0.1165   0.8370   0.0756
  -5.000   0.0312   0.03795   0.03108  -0.1177   0.8296   0.0756
  -4.750   0.0508   0.03467   0.02738  -0.1184   0.8217   0.0750
  -4.500   0.0761   0.03192   0.02421  -0.1193   0.8163   0.0749
  -4.250   0.0955   0.03015   0.02214  -0.1187   0.8077   0.0751
  -4.000   0.1213   0.02876   0.02049  -0.1188   0.8014   0.0764
  -3.750   0.1458   0.02748   0.01894  -0.1186   0.7948   0.0777
  -3.500   0.1696   0.02625   0.01742  -0.1181   0.7874   0.0784
  -3.250   0.1979   0.02498   0.01583  -0.1182   0.7819   0.0787
  -3.000   0.2211   0.02409   0.01471  -0.1174   0.7741   0.0792
  -2.750   0.2480   0.02321   0.01359  -0.1171   0.7676   0.0799
  -2.500   0.2757   0.02244   0.01260  -0.1169   0.7616   0.0806
  -2.250   0.3000   0.02191   0.01191  -0.1161   0.7537   0.0818
  -2.000   0.3288   0.02138   0.01118  -0.1160   0.7478   0.0835
  -1.750   0.3534   0.02089   0.01062  -0.1153   0.7403   0.0848
  -1.500   0.3796   0.02036   0.01006  -0.1148   0.7333   0.0860
  -1.250   0.4079   0.01989   0.00954  -0.1146   0.7275   0.0873
  -1.000   0.4310   0.01961   0.00929  -0.1137   0.7190   0.0886
  -0.750   0.4589   0.01926   0.00890  -0.1134   0.7128   0.0903
  -0.500   0.4830   0.01906   0.00869  -0.1125   0.7050   0.0922
  -0.250   0.5088   0.01884   0.00844  -0.1119   0.6976   0.0948
   0.000   0.5356   0.01864   0.00820  -0.1115   0.6910   0.0986
   0.250   0.5592   0.01851   0.00813  -0.1106   0.6825   0.1032
   0.500   0.5877   0.01831   0.00788  -0.1104   0.6763   0.1086
   0.750   0.6109   0.01827   0.00790  -0.1094   0.6673   0.1150
   1.000   0.6387   0.01810   0.00778  -0.1091   0.6603   0.1298
   1.250   0.6636   0.01801   0.00784  -0.1085   0.6520   0.1737
   1.500   0.6903   0.01769   0.00782  -0.1083   0.6443   0.2704
   2.000   0.7650   0.01632   0.00793  -0.1118   0.6276   1.0000
   2.250   0.7890   0.01648   0.00799  -0.1109   0.6192   1.0000
   2.500   0.8135   0.01662   0.00803  -0.1101   0.6107   1.0000
   2.750   0.8374   0.01680   0.00813  -0.1092   0.6020   1.0000
   3.000   0.8619   0.01695   0.00818  -0.1083   0.5934   1.0000
   3.250   0.8852   0.01715   0.00833  -0.1073   0.5843   1.0000
   3.500   0.9100   0.01730   0.00839  -0.1066   0.5758   1.0000
   3.750   0.9326   0.01753   0.00859  -0.1055   0.5662   1.0000
   4.000   0.9579   0.01768   0.00865  -0.1048   0.5579   1.0000
   4.250   0.9794   0.01795   0.00892  -0.1036   0.5478   1.0000
   4.500   1.0045   0.01813   0.00901  -0.1029   0.5396   1.0000
   4.750   1.0256   0.01843   0.00933  -0.1016   0.5294   1.0000
   5.000   1.0496   0.01867   0.00951  -0.1008   0.5210   1.0000
   5.250   1.0711   0.01897   0.00982  -0.0996   0.5114   1.0000
   5.500   1.0940   0.01925   0.01009  -0.0987   0.5026   1.0000
   5.750   1.1157   0.01957   0.01040  -0.0975   0.4933   1.0000
   6.000   1.1374   0.01990   0.01073  -0.0964   0.4843   1.0000
   6.250   1.1590   0.02023   0.01107  -0.0953   0.4753   1.0000
   6.500   1.1796   0.02061   0.01148  -0.0940   0.4662   1.0000
   6.750   1.2011   0.02095   0.01181  -0.0929   0.4574   1.0000
   7.000   1.2200   0.02137   0.01229  -0.0914   0.4479   1.0000
   7.250   1.2415   0.02173   0.01263  -0.0903   0.4395   1.0000
   7.500   1.2591   0.02220   0.01319  -0.0887   0.4302   1.0000
   7.750   1.2803   0.02259   0.01356  -0.0875   0.4222   1.0000
   8.000   1.2961   0.02310   0.01418  -0.0856   0.4125   1.0000
   8.250   1.3157   0.02353   0.01459  -0.0843   0.4043   1.0000
   8.500   1.3299   0.02408   0.01525  -0.0822   0.3944   1.0000
   8.750   1.3457   0.02457   0.01576  -0.0803   0.3852   1.0000
   9.000   1.3570   0.02509   0.01632  -0.0777   0.3747   1.0000
   9.250   1.3667   0.02570   0.01699  -0.0749   0.3641   1.0000
   9.500   1.3779   0.02628   0.01756  -0.0724   0.3540   1.0000
   9.750   1.3864   0.02700   0.01837  -0.0698   0.3436   1.0000
  10.000   1.3957   0.02774   0.01916  -0.0673   0.3338   1.0000
  10.250   1.4042   0.02853   0.01996  -0.0648   0.3238   1.0000
  10.500   1.4100   0.02949   0.02102  -0.0623   0.3130   1.0000
  10.750   1.4160   0.03048   0.02205  -0.0598   0.3024   1.0000
  11.000   1.4204   0.03160   0.02319  -0.0574   0.2915   1.0000
  11.250   1.4239   0.03289   0.02458  -0.0551   0.2804   1.0000
  11.500   1.4269   0.03427   0.02601  -0.0530   0.2693   1.0000
  11.750   1.4281   0.03583   0.02758  -0.0508   0.2579   1.0000
  12.000   1.4283   0.03761   0.02946  -0.0489   0.2457   1.0000
  12.250   1.4276   0.03956   0.03147  -0.0472   0.2333   1.0000
  12.500   1.4258   0.04171   0.03367  -0.0456   0.2207   1.0000
  12.750   1.4225   0.04410   0.03610  -0.0442   0.2077   1.0000
  13.000   1.4174   0.04678   0.03882  -0.0429   0.1935   1.0000
  13.250   1.4108   0.04978   0.04185  -0.0419   0.1780   1.0000
  13.500   1.4025   0.05311   0.04521  -0.0411   0.1614   1.0000
  13.750   1.3917   0.05690   0.04898  -0.0406   0.1441   1.0000
  14.000   1.3790   0.06113   0.05317  -0.0404   0.1284   1.0000
  14.250   1.3657   0.06564   0.05765  -0.0405   0.1156   1.0000
  14.500   1.3526   0.07036   0.06236  -0.0409   0.1056   1.0000
  15.000   1.3282   0.08011   0.07217  -0.0423   0.0913   1.0000
  15.250   1.3152   0.08531   0.07738  -0.0433   0.0863   1.0000
  15.500   1.3073   0.08990   0.08206  -0.0443   0.0811   1.0000
  15.750   1.2975   0.09482   0.08703  -0.0454   0.0770   1.0000
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