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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 50,000
Max Cl/Cd: 41.11 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe804-il-50000-n5.txt
Download as CSV file: xf-goe804-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3846   0.12844   0.12214  -0.0225   1.0000   0.0614
  -7.500  -0.3931   0.12763   0.12141  -0.0214   1.0000   0.0615
  -7.250  -0.4016   0.12674   0.12060  -0.0203   1.0000   0.0617
  -7.000  -0.4070   0.12547   0.11942  -0.0206   1.0000   0.0618
  -6.750  -0.3982   0.11944   0.11340  -0.0178   1.0000   0.0627
  -6.500  -0.3939   0.11558   0.10957  -0.0161   1.0000   0.0639
  -6.250  -0.3937   0.11291   0.10694  -0.0150   1.0000   0.0651
  -6.000  -0.3940   0.11052   0.10460  -0.0144   1.0000   0.0663
  -5.750  -0.3938   0.10816   0.10229  -0.0142   1.0000   0.0680
  -5.500  -0.3926   0.10578   0.09997  -0.0147   1.0000   0.0696
  -5.250  -0.3891   0.10360   0.09783  -0.0171   1.0000   0.0722
  -5.000  -0.3659   0.10144   0.09566  -0.0285   0.9975   0.0742
  -4.750  -0.3481   0.09656   0.09080  -0.0316   0.9939   0.0755
  -4.500  -0.3388   0.09245   0.08667  -0.0294   0.9908   0.0788
  -4.250  -0.3147   0.08867   0.08285  -0.0345   0.9867   0.0828
  -4.000  -0.2591   0.08469   0.07867  -0.0530   0.9811   0.0888
  -3.750  -0.2298   0.07983   0.07377  -0.0587   0.9779   0.0899
  -3.500  -0.2158   0.07593   0.06988  -0.0583   0.9739   0.0920
  -3.250  -0.1844   0.07214   0.06598  -0.0635   0.9703   0.0979
  -3.000  -0.0950   0.06372   0.05700  -0.0852   0.9689   0.0613
  -2.750  -0.0645   0.05972   0.05293  -0.0889   0.9661   0.0570
  -2.500  -0.0010   0.05418   0.04702  -0.1010   0.9645   0.0538
  -2.250   0.0614   0.04965   0.04203  -0.1118   0.9630   0.0565
  -2.000   0.1311   0.04493   0.03661  -0.1232   0.9626   0.0584
  -1.750   0.1944   0.04125   0.03216  -0.1323   0.9620   0.0642
  -1.500   0.2487   0.03889   0.02894  -0.1385   0.9607   0.0743
  -1.250   0.2914   0.03749   0.02712  -0.1424   0.9586   0.0870
  -1.000   0.3348   0.03641   0.02546  -0.1459   0.9566   0.1031
  -0.750   0.3709   0.03555   0.02430  -0.1481   0.9536   0.1146
  -0.500   0.4015   0.03518   0.02364  -0.1490   0.9492   0.1305
  -0.250   0.4335   0.03483   0.02308  -0.1500   0.9456   0.1393
   0.000   0.4681   0.03474   0.02281  -0.1516   0.9425   0.1549
   0.250   0.4957   0.03473   0.02271  -0.1521   0.9373   0.1711
   0.500   0.5276   0.03474   0.02264  -0.1533   0.9326   0.1909
   0.750   0.5655   0.03466   0.02270  -0.1560   0.9293   0.2394
   1.000   0.5847   0.03313   0.02295  -0.1546   0.9240   1.0000
   1.250   0.6130   0.03368   0.02315  -0.1550   0.9177   1.0000
   1.500   0.6478   0.03425   0.02345  -0.1568   0.9134   1.0000
   1.750   0.6715   0.03479   0.02386  -0.1566   0.9052   1.0000
   2.250   0.7358   0.03554   0.02442  -0.1588   0.8883   1.0000
   2.500   0.7691   0.03583   0.02465  -0.1599   0.8797   1.0000
   2.750   0.8011   0.03613   0.02496  -0.1609   0.8712   1.0000
   3.000   0.8261   0.03662   0.02549  -0.1608   0.8622   1.0000
   3.250   0.8598   0.03695   0.02588  -0.1621   0.8558   1.0000
   3.500   0.8823   0.03749   0.02653  -0.1616   0.8457   1.0000
   3.750   0.9174   0.03771   0.02686  -0.1630   0.8394   1.0000
   4.000   0.9419   0.03807   0.02740  -0.1626   0.8281   1.0000
   4.250   0.9675   0.03833   0.02782  -0.1623   0.8161   1.0000
   4.500   0.9958   0.03839   0.02807  -0.1622   0.8038   1.0000
   4.750   1.0259   0.03825   0.02818  -0.1621   0.7908   1.0000
   5.000   1.0563   0.03798   0.02817  -0.1619   0.7768   1.0000
   5.250   1.0859   0.03766   0.02812  -0.1615   0.7620   1.0000
   5.500   1.1149   0.03734   0.02815  -0.1609   0.7471   1.0000
   5.750   1.1440   0.03704   0.02821  -0.1603   0.7329   1.0000
   6.000   1.1708   0.03662   0.02816  -0.1590   0.7149   1.0000
   6.250   1.2022   0.03561   0.02760  -0.1578   0.6943   1.0000
   6.500   1.2348   0.03403   0.02642  -0.1558   0.6612   1.0000
   6.750   1.2644   0.03263   0.02527  -0.1530   0.6022   1.0000
   7.000   1.2969   0.03155   0.02324  -0.1493   0.4225   1.0000
   7.250   1.2876   0.03456   0.02499  -0.1438   0.2643   1.0000
   7.500   1.2830   0.03789   0.02745  -0.1399   0.1426   1.0000
   7.750   1.2834   0.04144   0.03031  -0.1367   0.0809   1.0000
   8.000   1.2900   0.04437   0.03301  -0.1342   0.0607   1.0000
   8.250   1.3006   0.04686   0.03567  -0.1319   0.0503   1.0000
   8.500   1.3159   0.04920   0.03833  -0.1299   0.0438   1.0000
   8.750   1.3336   0.05159   0.04081  -0.1283   0.0385   1.0000
   9.000   1.3665   0.05393   0.04352  -0.1278   0.0343   1.0000
   9.250   1.3968   0.05688   0.04658  -0.1279   0.0309   1.0000
   9.500   1.4351   0.06090   0.05125  -0.1284   0.0287   1.0000
   9.750   1.4579   0.06540   0.05637  -0.1274   0.0279   1.0000
  10.000   1.4643   0.06966   0.06118  -0.1248   0.0272   1.0000
  10.250   1.4624   0.07381   0.06581  -0.1217   0.0268   1.0000
  10.500   1.4549   0.07801   0.07045  -0.1184   0.0263   1.0000
  10.750   1.4435   0.08233   0.07519  -0.1153   0.0260   1.0000
  11.000   1.4292   0.08686   0.08009  -0.1127   0.0258   1.0000
  11.250   1.4125   0.09170   0.08528  -0.1106   0.0257   1.0000
  11.500   1.3944   0.09686   0.09076  -0.1093   0.0258   1.0000
  11.750   1.3750   0.10242   0.09662  -0.1089   0.0259   1.0000
  12.000   1.3546   0.10847   0.10294  -0.1096   0.0260   1.0000
  12.250   1.3344   0.11493   0.10963  -0.1114   0.0263   1.0000
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