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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 200,000
Max Cl/Cd: 107.01 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe804-il-200000-n5.txt
Download as CSV file: xf-goe804-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1652   0.10128   0.09758  -0.0815   0.9556   0.0188
  -7.750  -0.1722   0.10014   0.09649  -0.0791   0.9489   0.0189
  -7.500  -0.1680   0.09616   0.09256  -0.0803   0.9459   0.0191
  -7.250  -0.1542   0.09162   0.08800  -0.0801   0.9449   0.0197
  -7.000  -0.1420   0.08846   0.08484  -0.0815   0.9431   0.0203
  -6.750  -0.1426   0.08663   0.08303  -0.0803   0.9386   0.0206
  -6.500  -0.1398   0.08448   0.08091  -0.0800   0.9335   0.0210
  -6.250  -0.1264   0.08138   0.07781  -0.0828   0.9305   0.0215
  -6.000  -0.1078   0.07791   0.07433  -0.0870   0.9284   0.0221
  -5.750  -0.1055   0.07576   0.07221  -0.0870   0.9224   0.0224
  -5.500  -0.0917   0.07269   0.06913  -0.0902   0.9181   0.0228
  -5.250  -0.0679   0.06878   0.06520  -0.0961   0.9154   0.0233
  -5.000  -0.0327   0.06283   0.05918  -0.1063   0.9135   0.0170
  -4.750  -0.0136   0.05912   0.05544  -0.1113   0.9066   0.0179
  -4.500   0.0167   0.05479   0.05105  -0.1175   0.9034   0.0171
  -4.250   0.0640   0.04893   0.04505  -0.1285   0.9016   0.0162
  -4.000   0.1287   0.04113   0.03698  -0.1437   0.9009   0.0152
  -3.750   0.2027   0.03293   0.02832  -0.1594   0.9013   0.0155
  -3.500   0.3006   0.02197   0.01594  -0.1790   0.9053   0.0181
  -3.250   0.3496   0.01931   0.01260  -0.1844   0.9057   0.0210
  -3.000   0.3852   0.01847   0.01150  -0.1863   0.9043   0.0252
  -2.750   0.4207   0.01773   0.01057  -0.1881   0.9031   0.0313
  -2.500   0.4550   0.01730   0.00998  -0.1895   0.9018   0.0404
  -2.250   0.4889   0.01701   0.00957  -0.1909   0.9006   0.0518
  -2.000   0.5226   0.01679   0.00924  -0.1922   0.8996   0.0618
  -1.750   0.5573   0.01650   0.00894  -0.1938   0.8987   0.0706
  -1.500   0.5834   0.01640   0.00878  -0.1936   0.8953   0.0757
  -1.250   0.6072   0.01641   0.00880  -0.1930   0.8908   0.0814
  -1.000   0.6393   0.01618   0.00853  -0.1940   0.8887   0.0866
  -0.750   0.6743   0.01585   0.00819  -0.1956   0.8870   0.0922
  -0.500   0.7117   0.01545   0.00777  -0.1975   0.8855   0.1016
  -0.250   0.7518   0.01496   0.00731  -0.2000   0.8841   0.1186
   0.250   0.8064   0.01466   0.00725  -0.2000   0.8738   0.1884
   0.500   0.8484   0.01389   0.00715  -0.2034   0.8720   0.4490
   0.750   0.8734   0.01283   0.00701  -0.2021   0.8698   0.8944
   1.000   0.8847   0.01284   0.00705  -0.1984   0.8609   1.0000
   1.250   0.9184   0.01270   0.00688  -0.1995   0.8576   1.0000
   1.500   0.9549   0.01253   0.00669  -0.2012   0.8553   1.0000
   1.750   0.9733   0.01270   0.00688  -0.1993   0.8464   1.0000
   2.000   1.0094   0.01243   0.00662  -0.2008   0.8415   1.0000
   2.250   1.0299   0.01251   0.00673  -0.1991   0.8314   1.0000
   2.500   1.0592   0.01234   0.00659  -0.1992   0.8215   1.0000
   2.750   1.0876   0.01217   0.00647  -0.1990   0.8084   1.0000
   3.000   1.1153   0.01207   0.00640  -0.1988   0.7942   1.0000
   3.250   1.1440   0.01199   0.00638  -0.1987   0.7783   1.0000
   3.500   1.1766   0.01186   0.00629  -0.1995   0.7588   1.0000
   3.750   1.2155   0.01169   0.00610  -0.2015   0.7312   1.0000
   4.000   1.2520   0.01170   0.00598  -0.2029   0.6887   1.0000
   4.250   1.2790   0.01205   0.00616  -0.2025   0.6445   1.0000
   4.500   1.2991   0.01262   0.00653  -0.2007   0.5950   1.0000
   4.750   1.3055   0.01372   0.00716  -0.1963   0.4971   1.0000
   5.000   1.3013   0.01528   0.00808  -0.1901   0.4029   1.0000
   5.250   1.2986   0.01707   0.00915  -0.1846   0.2781   1.0000
   5.500   1.3043   0.01865   0.01024  -0.1810   0.2031   1.0000
   5.750   1.3127   0.02020   0.01128  -0.1779   0.1153   1.0000
   6.000   1.3228   0.02172   0.01245  -0.1751   0.0570   1.0000
   6.250   1.3357   0.02306   0.01364  -0.1727   0.0257   1.0000
   6.500   1.3506   0.02423   0.01486  -0.1704   0.0182   1.0000
   6.750   1.3647   0.02545   0.01620  -0.1681   0.0155   1.0000
   7.000   1.3788   0.02667   0.01758  -0.1658   0.0137   1.0000
   7.250   1.3924   0.02792   0.01894  -0.1636   0.0120   1.0000
   7.500   1.4032   0.02949   0.02063  -0.1610   0.0111   1.0000
   7.750   1.4150   0.03103   0.02233  -0.1585   0.0104   1.0000
   8.000   1.4266   0.03270   0.02414  -0.1560   0.0098   1.0000
   8.250   1.4388   0.03435   0.02586  -0.1539   0.0091   1.0000
   8.500   1.4518   0.03621   0.02785  -0.1518   0.0084   1.0000
   8.750   1.4676   0.03817   0.03004  -0.1500   0.0078   1.0000
   9.000   1.4853   0.04035   0.03242  -0.1485   0.0074   1.0000
   9.250   1.5039   0.04268   0.03496  -0.1472   0.0071   1.0000
   9.500   1.5212   0.04523   0.03774  -0.1458   0.0068   1.0000
   9.750   1.5365   0.04808   0.04086  -0.1443   0.0067   1.0000
  10.000   1.5457   0.05145   0.04461  -0.1419   0.0064   1.0000
  10.250   1.5473   0.05509   0.04882  -0.1384   0.0061   1.0000
  10.500   1.5451   0.05898   0.05315  -0.1349   0.0059   1.0000
  10.750   1.5381   0.06297   0.05758  -0.1313   0.0056   1.0000
  11.000   1.5276   0.06741   0.06239  -0.1278   0.0056   1.0000
  11.250   1.5133   0.07219   0.06754  -0.1246   0.0055   1.0000
  11.500   1.4971   0.07724   0.07293  -0.1219   0.0056   1.0000
  11.750   1.4792   0.08260   0.07859  -0.1200   0.0055   1.0000
  12.000   1.4594   0.08851   0.08480  -0.1188   0.0056   1.0000
  12.250   1.4390   0.09468   0.09124  -0.1187   0.0056   1.0000
  12.500   1.4182   0.10137   0.09819  -0.1197   0.0056   1.0000
  12.750   1.3989   0.10837   0.10540  -0.1219   0.0057   1.0000
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