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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 100,000
Max Cl/Cd: 67.6 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe804-il-100000-n5.txt
Download as CSV file: xf-goe804-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2779   0.10598   0.10130  -0.0445   0.9709   0.0365
  -6.750  -0.2714   0.10389   0.09923  -0.0470   0.9675   0.0375
  -6.500  -0.2731   0.10249   0.09788  -0.0479   0.9613   0.0381
  -6.250  -0.2576   0.09976   0.09517  -0.0545   0.9567   0.0385
  -6.000  -0.2462   0.09703   0.09245  -0.0595   0.9507   0.0387
  -5.750  -0.2252   0.09341   0.08881  -0.0665   0.9458   0.0388
  -5.500  -0.2185   0.08848   0.08391  -0.0637   0.9439   0.0395
  -5.250  -0.2037   0.08461   0.08003  -0.0638   0.9420   0.0408
  -5.000  -0.1963   0.08182   0.07726  -0.0647   0.9358   0.0413
  -4.750  -0.1752   0.07808   0.07350  -0.0692   0.9316   0.0422
  -4.500  -0.1451   0.07386   0.06922  -0.0761   0.9286   0.0427
  -4.250  -0.1190   0.06988   0.06519  -0.0820   0.9244   0.0427
  -4.000  -0.0597   0.06181   0.05686  -0.0986   0.9203   0.0278
  -3.750  -0.0113   0.05632   0.05118  -0.1088   0.9180   0.0280
  -3.500   0.0384   0.05083   0.04547  -0.1185   0.9166   0.0279
  -3.250   0.0936   0.04532   0.03967  -0.1288   0.9158   0.0274
  -3.000   0.1665   0.03848   0.03227  -0.1426   0.9168   0.0288
  -2.750   0.2143   0.03585   0.02931  -0.1489   0.9160   0.0317
  -2.500   0.2821   0.03101   0.02354  -0.1588   0.9173   0.0365
  -2.250   0.3319   0.02857   0.02043  -0.1641   0.9170   0.0424
  -2.000   0.3743   0.02712   0.01846  -0.1674   0.9159   0.0522
  -1.750   0.4122   0.02641   0.01747  -0.1698   0.9144   0.0648
  -1.500   0.4492   0.02596   0.01685  -0.1719   0.9130   0.0784
  -1.250   0.4726   0.02577   0.01646  -0.1713   0.9076   0.0874
  -1.000   0.5026   0.02549   0.01612  -0.1721   0.9041   0.0975
  -0.750   0.5360   0.02515   0.01565  -0.1733   0.9017   0.1046
  -0.500   0.5712   0.02480   0.01531  -0.1751   0.8997   0.1122
  -0.250   0.6077   0.02455   0.01505  -0.1770   0.8980   0.1249
   0.000   0.6279   0.02467   0.01519  -0.1759   0.8912   0.1380
   0.250   0.6601   0.02459   0.01515  -0.1770   0.8879   0.1607
   0.500   0.6966   0.02437   0.01505  -0.1790   0.8854   0.2173
   0.750   0.7136   0.02288   0.01521  -0.1766   0.8810   0.9509
   1.000   0.7390   0.02303   0.01523  -0.1762   0.8739   1.0000
   1.250   0.7751   0.02297   0.01506  -0.1777   0.8705   1.0000
   1.500   0.7994   0.02316   0.01519  -0.1771   0.8626   1.0000
   1.750   0.8328   0.02309   0.01507  -0.1781   0.8576   1.0000
   2.000   0.8693   0.02287   0.01484  -0.1795   0.8536   1.0000
   2.250   0.8929   0.02295   0.01493  -0.1786   0.8438   1.0000
   2.500   0.9308   0.02254   0.01455  -0.1801   0.8394   1.0000
   2.750   0.9530   0.02266   0.01473  -0.1790   0.8291   1.0000
   3.000   0.9893   0.02230   0.01443  -0.1802   0.8251   1.0000
   3.250   1.0098   0.02252   0.01476  -0.1788   0.8144   1.0000
   3.750   1.0655   0.02234   0.01481  -0.1783   0.7990   1.0000
   4.000   1.0890   0.02237   0.01500  -0.1773   0.7881   1.0000
   4.250   1.1188   0.02202   0.01480  -0.1771   0.7781   1.0000
   4.500   1.1453   0.02170   0.01463  -0.1762   0.7630   1.0000
   4.750   1.1712   0.02134   0.01446  -0.1750   0.7424   1.0000
   5.000   1.2056   0.02064   0.01392  -0.1752   0.7202   1.0000
   5.250   1.2425   0.01997   0.01339  -0.1757   0.6908   1.0000
   5.500   1.2880   0.01921   0.01271  -0.1777   0.6415   1.0000
   5.750   1.3242   0.01959   0.01223  -0.1778   0.4790   1.0000
   6.000   1.3206   0.02185   0.01339  -0.1721   0.3250   1.0000
   6.250   1.3197   0.02414   0.01484  -0.1676   0.2121   1.0000
   6.500   1.3236   0.02645   0.01639  -0.1642   0.1021   1.0000
   6.750   1.3301   0.02868   0.01822  -0.1609   0.0476   1.0000
   7.000   1.3418   0.03035   0.01989  -0.1582   0.0324   1.0000
   7.250   1.3532   0.03199   0.02167  -0.1555   0.0274   1.0000
   7.500   1.3640   0.03363   0.02349  -0.1529   0.0238   1.0000
   7.750   1.3707   0.03574   0.02577  -0.1498   0.0210   1.0000
   8.000   1.3787   0.03797   0.02818  -0.1468   0.0198   1.0000
   8.250   1.3916   0.03999   0.03040  -0.1445   0.0186   1.0000
   8.500   1.4068   0.04197   0.03254  -0.1427   0.0169   1.0000
   8.750   1.4226   0.04426   0.03492  -0.1412   0.0155   1.0000
   9.000   1.4499   0.04743   0.03831  -0.1411   0.0148   1.0000
   9.250   1.4779   0.05073   0.04205  -0.1407   0.0143   1.0000
   9.500   1.4957   0.05407   0.04586  -0.1391   0.0135   1.0000
   9.750   1.5053   0.05725   0.04944  -0.1368   0.0128   1.0000
  10.000   1.5097   0.06037   0.05289  -0.1341   0.0122   1.0000
  10.250   1.5108   0.06384   0.05669  -0.1311   0.0120   1.0000
  10.500   1.5071   0.06771   0.06094  -0.1278   0.0119   1.0000
  10.750   1.4993   0.07177   0.06537  -0.1245   0.0118   1.0000
  11.000   1.4874   0.07610   0.07008  -0.1212   0.0118   1.0000
  11.250   1.4721   0.08076   0.07512  -0.1183   0.0118   1.0000
  11.500   1.4537   0.08584   0.08058  -0.1159   0.0119   1.0000
  11.750   1.4341   0.09128   0.08637  -0.1143   0.0120   1.0000
  12.000   1.4129   0.09727   0.09270  -0.1137   0.0121   1.0000
  12.250   1.3910   0.10367   0.09940  -0.1143   0.0122   1.0000
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