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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 200,000
Max Cl/Cd: 39.8 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe05k-il-200000-n5.txt
Download as CSV file: xf-goe05k-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 5K AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5223   0.09858   0.09501  -0.0117   1.0000   0.0093
  -8.000  -0.5214   0.09552   0.09199  -0.0130   1.0000   0.0093
  -7.750  -0.5225   0.09265   0.08918  -0.0142   1.0000   0.0093
  -7.500  -0.5204   0.08942   0.08599  -0.0161   1.0000   0.0093
  -7.250  -0.5191   0.08540   0.08199  -0.0150   1.0000   0.0095
  -7.000  -0.5160   0.08192   0.07852  -0.0158   1.0000   0.0099
  -6.750  -0.5108   0.07832   0.07494  -0.0179   1.0000   0.0101
  -6.500  -0.5035   0.07467   0.07129  -0.0201   1.0000   0.0104
  -6.250  -0.4944   0.07088   0.06748  -0.0225   1.0000   0.0107
  -6.000  -0.4834   0.06698   0.06355  -0.0248   1.0000   0.0111
  -5.750  -0.4701   0.06307   0.05959  -0.0271   1.0000   0.0116
  -5.500  -0.4535   0.05912   0.05554  -0.0293   1.0000   0.0122
  -5.250  -0.4299   0.05528   0.05151  -0.0318   1.0000   0.0127
  -5.000  -0.4083   0.05181   0.04782  -0.0328   1.0000   0.0128
  -4.750  -0.3980   0.04738   0.04334  -0.0328   1.0000   0.0132
  -4.500  -0.3858   0.04389   0.03975  -0.0326   1.0000   0.0140
  -4.250  -0.3674   0.04070   0.03638  -0.0324   1.0000   0.0151
  -4.000  -0.3452   0.03779   0.03322  -0.0319   1.0000   0.0165
  -3.750  -0.3172   0.03686   0.03188  -0.0305   1.0000   0.0180
  -3.500  -0.3021   0.03144   0.02624  -0.0304   1.0000   0.0194
  -3.250  -0.2843   0.02880   0.02345  -0.0300   1.0000   0.0233
  -3.000  -0.2584   0.02709   0.02111  -0.0283   1.0000   0.0290
  -2.750  -0.2385   0.02407   0.01802  -0.0279   1.0000   0.0329
  -2.250  -0.1824   0.01852   0.01149  -0.0244   1.0000   0.0097
  -2.000  -0.1524   0.01655   0.00917  -0.0242   0.9990   0.0087
  -1.750  -0.1220   0.01486   0.00716  -0.0241   0.9978   0.0084
  -1.500  -0.0917   0.01352   0.00556  -0.0241   0.9964   0.0091
  -1.250  -0.0622   0.01249   0.00446  -0.0245   0.9945   0.0114
  -1.000  -0.0322   0.01166   0.00348  -0.0249   0.9921   0.0148
  -0.750  -0.0014   0.01096   0.00280  -0.0254   0.9897   0.0604
  -0.500   0.0358   0.00821   0.00266  -0.0279   0.9946   1.0000
  -0.250   0.0684   0.00829   0.00253  -0.0292   0.9912   1.0000
   0.000   0.1019   0.00840   0.00251  -0.0308   0.9883   1.0000
   0.250   0.1334   0.00847   0.00248  -0.0319   0.9845   1.0000
   0.500   0.1662   0.00856   0.00253  -0.0332   0.9808   1.0000
   0.750   0.1987   0.00865   0.00263  -0.0345   0.9774   1.0000
   1.000   0.2299   0.00871   0.00272  -0.0355   0.9724   1.0000
   1.250   0.2673   0.00877   0.00287  -0.0378   0.9683   1.0000
   1.500   0.3020   0.00873   0.00296  -0.0394   0.9592   1.0000
   1.750   0.3423   0.00860   0.00311  -0.0419   0.9478   1.0000
   2.000   0.4063   0.01158   0.00254  -0.0478   0.0179   1.0000
   2.250   0.4287   0.01229   0.00347  -0.0463   0.0119   1.0000
   2.500   0.4501   0.01318   0.00449  -0.0449   0.0091   1.0000
   2.750   0.4712   0.01434   0.00576  -0.0431   0.0085   1.0000
   3.000   0.4934   0.01578   0.00727  -0.0416   0.0077   1.0000
   3.250   0.5176   0.01746   0.00915  -0.0404   0.0069   1.0000
   3.500   0.5433   0.01944   0.01139  -0.0392   0.0070   1.0000
   3.750   0.5698   0.02165   0.01401  -0.0377   0.0080   1.0000
   4.000   0.5935   0.02455   0.01727  -0.0360   0.0097   1.0000
   4.500   0.6450   0.03121   0.02494  -0.0308   0.0260   1.0000
   4.750   0.6641   0.03404   0.02811  -0.0289   0.0231   1.0000
   5.000   0.6792   0.03755   0.03179  -0.0276   0.0210   1.0000
   5.250   0.6860   0.04421   0.03871  -0.0260   0.0196   1.0000
   5.500   0.7129   0.04442   0.03946  -0.0234   0.0171   1.0000
   5.750   0.7284   0.04783   0.04314  -0.0219   0.0155   1.0000
   6.250   0.7414   0.05731   0.05280  -0.0201   0.0138   1.0000
   7.250   0.7140   0.06196   0.05867  -0.0141   0.0132   1.0000
   7.500   0.7089   0.06665   0.06345  -0.0146   0.0130   1.0000
   7.750   0.6982   0.07083   0.06767  -0.0144   0.0131   1.0000
   8.000   0.6862   0.07529   0.07215  -0.0156   0.0132   1.0000
   8.250   0.6756   0.08030   0.07715  -0.0184   0.0134   1.0000
   8.500   0.6682   0.08543   0.08227  -0.0211   0.0134   1.0000
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