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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 500,000
Max Cl/Cd: 169.11 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe804-il-500000.txt
Download as CSV file: xf-goe804-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 804 (EA 8) AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2099   0.09449   0.09212  -0.0736   0.9672   0.0165
  -7.750  -0.2008   0.09135   0.08899  -0.0763   0.9643   0.0165
  -7.500  -0.1922   0.08650   0.08415  -0.0777   0.9629   0.0170
  -7.250  -0.1767   0.08393   0.08158  -0.0787   0.9620   0.0177
  -7.000  -0.1610   0.08101   0.07865  -0.0821   0.9607   0.0183
  -6.750  -0.1707   0.07982   0.07749  -0.0786   0.9530   0.0187
  -6.500  -0.1525   0.07628   0.07394  -0.0831   0.9505   0.0196
  -6.250  -0.1264   0.07202   0.06967  -0.0909   0.9488   0.0214
  -6.000  -0.1143   0.06916   0.06681  -0.0971   0.9413   0.0223
  -5.750  -0.0866   0.06488   0.06249  -0.1046   0.9386   0.0224
  -5.500  -0.0619   0.05801   0.05560  -0.1129   0.9369   0.0231
  -5.250  -0.0350   0.05498   0.05253  -0.1167   0.9360   0.0238
  -5.000   0.0003   0.05140   0.04891  -0.1232   0.9351   0.0248
  -4.750   0.0133   0.04882   0.04629  -0.1244   0.9276   0.0258
  -4.500   0.0812   0.04242   0.03963  -0.1394   0.9263   0.0300
  -4.250   0.2160   0.01702   0.01227  -0.1764   0.9357   0.0235
  -4.000   0.2553   0.01609   0.01118  -0.1792   0.9353   0.0254
  -3.750   0.2941   0.01505   0.00990  -0.1818   0.9350   0.0278
  -3.500   0.3256   0.01452   0.00918  -0.1827   0.9336   0.0306
  -3.250   0.3440   0.01403   0.00862  -0.1811   0.9287   0.0333
  -3.000   0.3767   0.01375   0.00828  -0.1821   0.9272   0.0370
  -2.750   0.4128   0.01314   0.00756  -0.1840   0.9263   0.0420
  -2.500   0.4498   0.01273   0.00715  -0.1859   0.9252   0.0476
  -2.250   0.4882   0.01247   0.00683  -0.1879   0.9243   0.0520
  -2.000   0.5310   0.01152   0.00586  -0.1913   0.9240   0.0603
  -1.750   0.5714   0.01113   0.00543  -0.1938   0.9234   0.0652
  -1.500   0.6103   0.01061   0.00494  -0.1963   0.9229   0.0710
  -1.250   0.6474   0.01033   0.00466  -0.1983   0.9222   0.0762
  -1.000   0.6868   0.00992   0.00425  -0.2008   0.9213   0.0811
  -0.750   0.7063   0.00989   0.00427  -0.1989   0.9151   0.0871
  -0.500   0.7413   0.00960   0.00402  -0.2004   0.9129   0.0992
  -0.250   0.7776   0.00925   0.00376  -0.2022   0.9111   0.1267
   0.000   0.8172   0.00878   0.00353  -0.2049   0.9092   0.2182
   0.250   0.8610   0.00749   0.00365  -0.2089   0.9075   0.7934
   0.500   0.8772   0.00739   0.00369  -0.2059   0.8995   0.8782
   0.750   0.9053   0.00704   0.00337  -0.2053   0.8941   0.9245
   1.000   0.9203   0.00686   0.00324  -0.2020   0.8858   1.0000
   1.250   0.9540   0.00675   0.00310  -0.2031   0.8806   1.0000
   1.500   0.9798   0.00676   0.00312  -0.2026   0.8727   1.0000
   1.750   1.0117   0.00668   0.00301  -0.2033   0.8659   1.0000
   2.000   1.0363   0.00671   0.00306  -0.2025   0.8562   1.0000
   2.250   1.0632   0.00669   0.00303  -0.2021   0.8444   1.0000
   2.500   1.0898   0.00668   0.00304  -0.2016   0.8305   1.0000
   2.750   1.1160   0.00670   0.00304  -0.2011   0.8133   1.0000
   3.000   1.1415   0.00675   0.00300  -0.2003   0.7808   1.0000
   3.250   1.1639   0.00703   0.00303  -0.1988   0.7265   1.0000
   3.500   1.1807   0.00763   0.00329  -0.1963   0.6612   1.0000
   3.750   1.1929   0.00846   0.00371  -0.1929   0.5846   1.0000
   4.000   1.1970   0.00978   0.00434  -0.1882   0.4550   1.0000
   4.250   1.2100   0.01084   0.00494  -0.1854   0.3743   1.0000
   4.500   1.2226   0.01206   0.00557  -0.1828   0.2625   1.0000
   4.750   1.2405   0.01291   0.00614  -0.1811   0.2127   1.0000
   5.000   1.2592   0.01373   0.00668  -0.1795   0.1495   1.0000
   5.250   1.2756   0.01478   0.00739  -0.1776   0.0925   1.0000
   5.500   1.2947   0.01553   0.00796  -0.1761   0.0647   1.0000
   5.750   1.3149   0.01614   0.00856  -0.1747   0.0529   1.0000
   6.000   1.3343   0.01682   0.00923  -0.1732   0.0407   1.0000
   6.250   1.3534   0.01754   0.00993  -0.1716   0.0313   1.0000
   6.500   1.3711   0.01839   0.01076  -0.1697   0.0254   1.0000
   6.750   1.3895   0.01912   0.01157  -0.1679   0.0231   1.0000
   7.000   1.4077   0.01988   0.01239  -0.1662   0.0210   1.0000
   7.250   1.4236   0.02086   0.01341  -0.1641   0.0189   1.0000
   7.500   1.4351   0.02235   0.01504  -0.1611   0.0173   1.0000
   7.750   1.4525   0.02320   0.01597  -0.1593   0.0164   1.0000
   8.000   1.4686   0.02425   0.01712  -0.1573   0.0155   1.0000
   8.250   1.4844   0.02538   0.01835  -0.1553   0.0146   1.0000
   8.500   1.5000   0.02656   0.01960  -0.1533   0.0139   1.0000
   8.750   1.5150   0.02802   0.02114  -0.1513   0.0132   1.0000
   9.000   1.5360   0.03185   0.02522  -0.1506   0.0122   1.0000
   9.250   1.5506   0.03258   0.02609  -0.1484   0.0118   1.0000
   9.500   1.5671   0.03400   0.02767  -0.1467   0.0113   1.0000
   9.750   1.5840   0.03603   0.02992  -0.1451   0.0108   1.0000
  10.000   1.5988   0.03829   0.03242  -0.1432   0.0105   1.0000
  10.250   1.6105   0.04095   0.03535  -0.1409   0.0103   1.0000
  10.500   1.6176   0.04356   0.03822  -0.1380   0.0100   1.0000
  10.750   1.6213   0.04613   0.04102  -0.1349   0.0097   1.0000
  11.000   1.6212   0.04906   0.04422  -0.1314   0.0096   1.0000
  11.250   1.6143   0.05300   0.04850  -0.1273   0.0095   1.0000
  11.500   1.5982   0.05808   0.05400  -0.1226   0.0096   1.0000
  11.750   1.5701   0.06489   0.06129  -0.1176   0.0098   1.0000
  12.000   1.5345   0.07276   0.06959  -0.1134   0.0101   1.0000
  12.250   1.5020   0.08024   0.07740  -0.1109   0.0103   1.0000
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