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GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 440 AIRFOIL (goe440-il)
Reynolds number: 200,000
Max Cl/Cd: 71.11 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe440-il-200000.txt
Download as CSV file: xf-goe440-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 440 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.3033   0.09894   0.09595  -0.1196   0.8475   0.0122
 -10.250   0.3095   0.09640   0.09339  -0.1198   0.8390   0.0125
 -10.000   0.2313   0.11600   0.11297  -0.1182   0.8806   0.0106
  -9.750   0.2411   0.11179   0.10873  -0.1175   0.8714   0.0110
  -9.500   0.2494   0.10882   0.10570  -0.1176   0.8629   0.0114
  -9.250   0.2574   0.10620   0.10307  -0.1180   0.8526   0.0118
  -9.000   0.2655   0.10365   0.10049  -0.1185   0.8422   0.0122
  -8.750   0.2739   0.10114   0.09795  -0.1191   0.8326   0.0126
  -8.500   0.2827   0.09864   0.09539  -0.1198   0.8235   0.0130
  -8.250   0.2913   0.09620   0.09294  -0.1206   0.8127   0.0135
  -8.000   0.3003   0.09376   0.09045  -0.1215   0.8028   0.0140
  -7.750   0.3096   0.09130   0.08793  -0.1224   0.7939   0.0145
  -7.500   0.3188   0.08892   0.08551  -0.1233   0.7834   0.0151
  -7.250   0.3282   0.08655   0.08311  -0.1244   0.7733   0.0157
  -7.000   0.3380   0.08419   0.08067  -0.1254   0.7641   0.0163
  -6.750   0.3479   0.08188   0.07832  -0.1266   0.7542   0.0170
  -6.500   0.3579   0.07967   0.07608  -0.1279   0.7443   0.0177
  -6.250   0.3684   0.07761   0.07395  -0.1295   0.7352   0.0184
  -6.000   0.3774   0.07599   0.07229  -0.1312   0.7255   0.0189
  -5.750   0.3881   0.07449   0.07077  -0.1340   0.7156   0.0192
  -5.500   0.4053   0.07248   0.06869  -0.1385   0.7066   0.0195
  -5.250   0.4247   0.07013   0.06631  -0.1432   0.6968   0.0196
  -5.000   0.4459   0.06753   0.06366  -0.1481   0.6867   0.0197
  -4.750   0.4684   0.06436   0.06044  -0.1531   0.6778   0.0198
  -4.500   0.4642   0.06054   0.05659  -0.1474   0.6687   0.0212
  -4.250   0.4798   0.05799   0.05399  -0.1489   0.6587   0.0226
  -4.000   0.5026   0.05522   0.05112  -0.1532   0.6491   0.0243
  -3.750   0.5305   0.05218   0.04801  -0.1591   0.6384   0.0264
  -3.500   0.5828   0.04817   0.04387  -0.1726   0.6268   0.0292
  -3.250   0.6521   0.04345   0.03871  -0.1895   0.6153   0.0298
  -3.000   0.6561   0.04018   0.03555  -0.1867   0.6058   0.0319
  -2.750   0.6975   0.03681   0.03196  -0.1936   0.5941   0.0360
  -2.500   0.7561   0.03235   0.02705  -0.2043   0.5822   0.0417
  -2.000   0.8461   0.02725   0.02105  -0.2157   0.5597   0.0673
  -1.750   0.8831   0.02526   0.01878  -0.2194   0.5494   0.0969
  -1.250   0.9660   0.02181   0.01423  -0.2234   0.5310   0.0621
  -1.000   1.0031   0.02032   0.01219  -0.2234   0.5225   0.0289
  -0.750   1.0375   0.01906   0.01067  -0.2246   0.5145   0.0253
  -0.500   1.0705   0.01837   0.00981  -0.2255   0.5068   0.0259
  -0.250   1.1047   0.01798   0.00921  -0.2271   0.4996   0.0378
   0.000   1.1426   0.01700   0.00939  -0.2300   0.4924   0.5545
   0.250   1.1690   0.01722   0.00949  -0.2300   0.4861   0.6148
   0.500   1.1940   0.01735   0.00962  -0.2298   0.4795   0.6751
   0.750   1.2169   0.01746   0.00965  -0.2289   0.4743   0.7772
   1.000   1.2323   0.01736   0.00969  -0.2265   0.4688   1.0000
   1.250   1.2588   0.01771   0.00987  -0.2268   0.4632   1.0000
   1.500   1.2764   0.01795   0.00989  -0.2254   0.4472   1.0000
   1.750   1.2993   0.01829   0.01013  -0.2250   0.4393   1.0000
   2.000   1.3090   0.01860   0.01022  -0.2222   0.4164   1.0000
   2.250   1.3235   0.01901   0.01050  -0.2203   0.4006   1.0000
   2.500   1.3286   0.01953   0.01085  -0.2168   0.3725   1.0000
   2.750   1.3390   0.02015   0.01132  -0.2144   0.3506   1.0000
   3.000   1.3403   0.02135   0.01214  -0.2108   0.3057   1.0000
   3.250   1.3487   0.02243   0.01298  -0.2084   0.2782   1.0000
   3.500   1.3518   0.02393   0.01421  -0.2054   0.2413   1.0000
   3.750   1.3293   0.02736   0.01703  -0.1994   0.1616   1.0000
   4.000   1.3067   0.03109   0.02040  -0.1940   0.0798   1.0000
   4.250   1.3157   0.03250   0.02179  -0.1923   0.0377   1.0000
   4.500   1.3303   0.03347   0.02277  -0.1913   0.0420   1.0000
   4.750   1.4664   0.02538   0.01617  -0.2036   0.2771   1.0000
   5.000   1.4670   0.02713   0.01767  -0.2006   0.2456   1.0000
   5.250   1.4552   0.02992   0.02009  -0.1964   0.1992   1.0000
   5.500   1.4291   0.03407   0.02382  -0.1911   0.1375   1.0000
   5.750   1.4039   0.03849   0.02804  -0.1866   0.0754   1.0000
   6.000   1.4073   0.04060   0.03019  -0.1848   0.0445   1.0000
   6.250   1.4166   0.04220   0.03189  -0.1836   0.0423   1.0000
   6.500   1.4228   0.04415   0.03399  -0.1822   0.0403   1.0000
   6.750   1.4256   0.04650   0.03653  -0.1807   0.0381   1.0000
   7.000   1.4230   0.04951   0.03981  -0.1790   0.0359   1.0000
   7.250   1.4221   0.05249   0.04300  -0.1777   0.0330   1.0000
   7.500   1.4163   0.05613   0.04687  -0.1763   0.0295   1.0000
   7.750   1.4111   0.05980   0.05076  -0.1751   0.0256   1.0000
   8.000   1.3976   0.06468   0.05590  -0.1739   0.0240   1.0000
   8.250   1.3786   0.07048   0.06197  -0.1730   0.0234   1.0000
   8.500   1.3575   0.07681   0.06854  -0.1724   0.0231   1.0000
   8.750   1.3353   0.08360   0.07555  -0.1722   0.0229   1.0000
   9.000   1.3665   0.08255   0.07446  -0.1717   0.0192   1.0000
   9.250   1.3510   0.08849   0.08059  -0.1716   0.0187   1.0000
   9.500   1.3343   0.09477   0.08705  -0.1718   0.0184   1.0000
   9.750   1.3165   0.10135   0.09380  -0.1721   0.0182   1.0000
  10.000   1.2989   0.10807   0.10069  -0.1727   0.0181   1.0000
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