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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 50,000
Max Cl/Cd: 29.15 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe174-il-50000.txt
Download as CSV file: xf-goe174-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 174 (ALBATROS 5020) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2954   0.10443   0.09799  -0.0231   1.0000   0.1557
  -7.500  -0.3111   0.10498   0.09874  -0.0242   1.0000   0.1582
  -7.250  -0.2975   0.09963   0.09343  -0.0219   1.0000   0.1627
  -7.000  -0.2955   0.09727   0.09117  -0.0213   1.0000   0.1691
  -6.750  -0.3073   0.09771   0.09177  -0.0248   1.0000   0.1731
  -6.500  -0.2971   0.09267   0.08679  -0.0211   1.0000   0.1779
  -6.250  -0.2980   0.09084   0.08506  -0.0208   1.0000   0.1855
  -6.000  -0.3047   0.08985   0.08421  -0.0232   1.0000   0.1895
  -5.750  -0.3000   0.08627   0.08070  -0.0187   1.0000   0.1976
  -5.500  -0.3056   0.08573   0.08026  -0.0226   1.0000   0.2040
  -5.250  -0.3037   0.08220   0.07682  -0.0173   1.0000   0.2112
  -5.000  -0.3046   0.08080   0.07548  -0.0200   1.0000   0.2195
  -4.750  -0.3041   0.07818   0.07295  -0.0167   1.0000   0.2274
  -4.500  -0.3022   0.07612   0.07094  -0.0177   1.0000   0.2361
  -4.250  -0.2964   0.07448   0.06931  -0.0202   1.0000   0.2488
  -4.000  -0.2953   0.07197   0.06688  -0.0173   1.0000   0.2583
  -3.750  -0.2898   0.06969   0.06464  -0.0173   1.0000   0.2707
  -3.500  -0.2819   0.06754   0.06249  -0.0178   1.0000   0.2876
  -3.250  -0.2712   0.06536   0.06031  -0.0193   1.0000   0.3113
  -3.000  -0.2615   0.06329   0.05826  -0.0194   1.0000   0.3411
  -2.750  -0.2551   0.06095   0.05599  -0.0175   1.0000   0.3725
  -2.250  -0.2167   0.05467   0.04986  -0.0138   0.9848   0.4965
  -2.000  -0.1947   0.05153   0.04677  -0.0115   0.9734   0.5698
  -1.750  -0.1720   0.04838   0.04367  -0.0091   0.9614   0.6230
  -1.500   0.1406   0.04125   0.03333  -0.0886   0.9417   0.1859
  -1.250   0.2044   0.03838   0.02981  -0.0955   0.9292   0.1684
  -1.000   0.2663   0.03609   0.02689  -0.1016   0.9167   0.1623
  -0.750   0.3206   0.03443   0.02460  -0.1058   0.9030   0.1581
  -0.500   0.3697   0.03309   0.02292  -0.1091   0.8886   0.1592
  -0.250   0.4179   0.03206   0.02171  -0.1120   0.8741   0.1679
   0.000   0.4667   0.03114   0.02059  -0.1147   0.8597   0.1846
   0.250   0.5111   0.03017   0.01961  -0.1164   0.8449   0.2100
   0.500   0.5495   0.02688   0.01841  -0.1169   0.8312   1.0000
   0.750   0.5881   0.02698   0.01778  -0.1173   0.8148   1.0000
   1.000   0.6238   0.02708   0.01754  -0.1176   0.7982   1.0000
   1.250   0.6577   0.02715   0.01735  -0.1176   0.7815   1.0000
   1.500   0.6899   0.02725   0.01724  -0.1172   0.7650   1.0000
   1.750   0.7157   0.02766   0.01749  -0.1163   0.7468   1.0000
   2.000   0.7415   0.02808   0.01776  -0.1153   0.7289   1.0000
   2.250   0.7685   0.02843   0.01800  -0.1144   0.7124   1.0000
   2.500   0.7953   0.02882   0.01828  -0.1136   0.6966   1.0000
   2.750   0.8216   0.02929   0.01864  -0.1127   0.6815   1.0000
   3.000   0.8471   0.02987   0.01913  -0.1119   0.6671   1.0000
   3.250   0.8722   0.03054   0.01976  -0.1111   0.6537   1.0000
   3.500   0.8988   0.03113   0.02027  -0.1104   0.6415   1.0000
   3.750   0.9254   0.03175   0.02083  -0.1097   0.6298   1.0000
   4.000   0.9441   0.03313   0.02225  -0.1089   0.6169   1.0000
   4.250   0.9627   0.03460   0.02379  -0.1081   0.6052   1.0000
   4.500   0.9886   0.03541   0.02458  -0.1075   0.5958   1.0000
   4.750   1.0074   0.03688   0.02612  -0.1068   0.5852   1.0000
   5.000   1.0197   0.03909   0.02845  -0.1059   0.5749   1.0000
   5.250   1.0503   0.03951   0.02889  -0.1055   0.5676   1.0000
   5.500   1.0525   0.04271   0.03226  -0.1045   0.5567   1.0000
   5.750   1.0687   0.04463   0.03428  -0.1037   0.5488   1.0000
   6.000   1.0775   0.04728   0.03705  -0.1029   0.5400   1.0000
   6.250   1.0740   0.05125   0.04115  -0.1020   0.5312   1.0000
   6.500   1.0939   0.05278   0.04280  -0.1013   0.5236   1.0000
   6.750   1.0519   0.06093   0.05100  -0.1006   0.5146   1.0000
   7.000   1.1329   0.05557   0.04579  -0.0992   0.5064   1.0000
   7.250   1.0245   0.07083   0.06098  -0.0996   0.4974   1.0000
   7.500   1.0362   0.07296   0.06323  -0.0986   0.4875   1.0000
   7.750   1.1267   0.06599   0.05651  -0.0955   0.4762   1.0000
   8.000   1.0210   0.08157   0.07194  -0.0978   0.4697   1.0000
   8.250   1.0508   0.08197   0.07248  -0.0964   0.4598   1.0000
   8.500   1.0147   0.08965   0.08015  -0.0974   0.4539   1.0000
   8.750   1.0365   0.09117   0.08179  -0.0964   0.4447   1.0000
   9.000   1.0072   0.09823   0.08886  -0.0975   0.4400   1.0000
   9.250   1.0396   0.09906   0.08986  -0.0963   0.4311   1.0000
   9.500   1.0165   0.10620   0.09702  -0.0979   0.4304   1.0000
   9.750   1.0135   0.11186   0.10277  -0.0993   0.4320   1.0000
  11.000   1.4845   0.05207   0.04514  -0.0678   0.2932   1.0000
  11.250   1.4017   0.06749   0.06078  -0.0661   0.3129   1.0000
  11.500   1.4635   0.05024   0.04337  -0.0569   0.2384   1.0000
  11.750   1.4381   0.05364   0.04692  -0.0540   0.2197   1.0000
  12.000   1.4154   0.05718   0.05033  -0.0523   0.1938   1.0000
  12.250   1.3945   0.06148   0.05428  -0.0515   0.1691   1.0000
  12.500   1.3755   0.06652   0.05910  -0.0512   0.1506   1.0000
  12.750   1.3609   0.07125   0.06359  -0.0509   0.1361   1.0000
  13.000   1.3504   0.07571   0.06790  -0.0505   0.1245   1.0000
  13.250   1.3446   0.07960   0.07164  -0.0497   0.1146   1.0000
  13.500   1.3417   0.08324   0.07529  -0.0491   0.1062   1.0000
  13.750   1.3399   0.08721   0.07940  -0.0485   0.1005   1.0000
  14.000   1.3391   0.09115   0.08353  -0.0482   0.0961   1.0000
  14.250   1.3519   0.09327   0.08561  -0.0461   0.0907   1.0000
  14.500   1.3387   0.09925   0.09192  -0.0477   0.0896   1.0000
  14.750   1.3220   0.10598   0.09894  -0.0500   0.0890   1.0000
  15.000   1.3011   0.11378   0.10700  -0.0535   0.0892   1.0000
  15.250   1.2772   0.12274   0.11617  -0.0580   0.0900   1.0000
  15.500   1.2523   0.13257   0.12616  -0.0633   0.0911   1.0000
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