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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 500,000
Max Cl/Cd: 98.41 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe188-il-500000.txt
Download as CSV file: xf-goe188-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2919   0.08642   0.08440  -0.0203   1.0000   0.0092
  -8.250  -0.2903   0.08282   0.08082  -0.0212   1.0000   0.0093
  -8.000  -0.2890   0.07923   0.07725  -0.0222   1.0000   0.0094
  -7.750  -0.2882   0.07562   0.07366  -0.0232   1.0000   0.0095
  -7.500  -0.2880   0.07205   0.07012  -0.0243   1.0000   0.0096
  -7.250  -0.2892   0.06854   0.06664  -0.0253   1.0000   0.0097
  -7.000  -0.2931   0.06524   0.06339  -0.0260   1.0000   0.0097
  -6.750  -0.3007   0.06216   0.06037  -0.0266   1.0000   0.0098
  -6.500  -0.2843   0.05640   0.05458  -0.0342   0.9871   0.0100
  -6.250  -0.2641   0.05050   0.04863  -0.0416   0.9618   0.0102
  -6.000  -0.2413   0.04471   0.04271  -0.0481   0.9263   0.0105
  -5.750  -0.2913   0.05814   0.05598  -0.0448   0.9827   0.0100
  -5.500  -0.2554   0.05311   0.05081  -0.0515   0.9565   0.0104
  -5.250  -0.2195   0.04850   0.04598  -0.0566   0.9171   0.0110
  -5.000  -0.1900   0.04523   0.04235  -0.0580   0.8798   0.0115
  -4.750  -0.1639   0.04244   0.03922  -0.0583   0.8560   0.0117
  -4.500  -0.1399   0.03966   0.03615  -0.0583   0.8381   0.0118
  -4.250  -0.1157   0.03689   0.03307  -0.0583   0.8227   0.0119
  -4.000  -0.0987   0.03185   0.02784  -0.0591   0.8099   0.0124
  -3.750  -0.0762   0.02964   0.02546  -0.0593   0.7982   0.0130
  -3.500  -0.0511   0.02757   0.02317  -0.0593   0.7880   0.0140
  -3.250  -0.0233   0.02564   0.02098  -0.0590   0.7776   0.0156
  -3.000   0.0088   0.02578   0.02076  -0.0578   0.7677   0.0171
  -2.750   0.0331   0.02159   0.01621  -0.0579   0.7593   0.0182
  -2.500   0.0593   0.01991   0.01440  -0.0581   0.7497   0.0191
  -2.250   0.0867   0.01860   0.01291  -0.0580   0.7409   0.0203
  -2.000   0.1149   0.01753   0.01161  -0.0577   0.7321   0.0222
  -1.750   0.1446   0.01788   0.01175  -0.0572   0.7224   0.0250
  -1.500   0.1719   0.01514   0.00874  -0.0572   0.7145   0.0278
  -1.250   0.1998   0.01427   0.00779  -0.0572   0.7057   0.0314
  -0.250   0.3136   0.01089   0.00396  -0.0558   0.6704   0.0314
   0.000   0.3421   0.01059   0.00354  -0.0554   0.6615   0.0258
   0.250   0.3700   0.01004   0.00296  -0.0553   0.6520   0.0246
   0.500   0.3981   0.00969   0.00255  -0.0552   0.6424   0.0250
   0.750   0.4262   0.00938   0.00212  -0.0552   0.6320   0.0275
   1.000   0.4545   0.00925   0.00192  -0.0552   0.6204   0.0328
   1.250   0.4808   0.00794   0.00186  -0.0557   0.6089   0.5524
   1.500   0.5084   0.00682   0.00183  -0.0551   0.5961   1.0000
   1.750   0.5358   0.00691   0.00180  -0.0550   0.5804   1.0000
   2.000   0.5630   0.00702   0.00179  -0.0549   0.5612   1.0000
   2.250   0.5903   0.00715   0.00180  -0.0548   0.5369   1.0000
   2.500   0.6173   0.00731   0.00184  -0.0547   0.5097   1.0000
   2.750   0.6439   0.00754   0.00190  -0.0546   0.4801   1.0000
   3.000   0.6705   0.00779   0.00200  -0.0544   0.4543   1.0000
   3.250   0.6972   0.00805   0.00212  -0.0544   0.4353   1.0000
   3.500   0.7242   0.00827   0.00228  -0.0543   0.4209   1.0000
   3.750   0.7513   0.00848   0.00243  -0.0543   0.4087   1.0000
   4.000   0.7785   0.00867   0.00258  -0.0544   0.3983   1.0000
   4.250   0.8056   0.00888   0.00275  -0.0544   0.3892   1.0000
   4.500   0.8326   0.00909   0.00295  -0.0544   0.3804   1.0000
   4.750   0.8599   0.00927   0.00313  -0.0544   0.3721   1.0000
   5.000   0.8866   0.00950   0.00333  -0.0544   0.3643   1.0000
   5.250   0.9137   0.00967   0.00351  -0.0544   0.3540   1.0000
   5.500   0.9406   0.00987   0.00371  -0.0544   0.3420   1.0000
   5.750   0.9674   0.01007   0.00391  -0.0544   0.3317   1.0000
   6.000   0.9938   0.01031   0.00414  -0.0543   0.3223   1.0000
   6.250   1.0208   0.01049   0.00436  -0.0544   0.3126   1.0000
   6.500   1.0474   0.01070   0.00461  -0.0543   0.3036   1.0000
   6.750   1.0736   0.01094   0.00487  -0.0543   0.2928   1.0000
   7.000   1.0998   0.01118   0.00512  -0.0542   0.2798   1.0000
   7.250   1.1258   0.01144   0.00540  -0.0541   0.2666   1.0000
   7.500   1.1515   0.01173   0.00571  -0.0540   0.2464   1.0000
   7.750   1.1754   0.01222   0.00607  -0.0537   0.2146   1.0000
   8.000   1.1971   0.01297   0.00661  -0.0531   0.1753   1.0000
   8.250   1.2183   0.01377   0.00726  -0.0525   0.1393   1.0000
   8.500   1.2347   0.01512   0.00823  -0.0513   0.0797   1.0000
   8.750   1.2548   0.01599   0.00903  -0.0505   0.0629   1.0000
   9.000   1.2764   0.01664   0.00972  -0.0498   0.0539   1.0000
   9.250   1.2975   0.01731   0.01040  -0.0491   0.0446   1.0000
   9.500   1.3159   0.01824   0.01124  -0.0481   0.0282   1.0000
   9.750   1.3313   0.01945   0.01237  -0.0466   0.0157   1.0000
  10.000   1.3467   0.02059   0.01364  -0.0450   0.0129   1.0000
  10.250   1.3616   0.02166   0.01484  -0.0434   0.0116   1.0000
  10.500   1.3727   0.02296   0.01625  -0.0414   0.0103   1.0000
  10.750   1.3722   0.02496   0.01844  -0.0379   0.0093   1.0000
  11.000   1.3781   0.02612   0.01972  -0.0351   0.0090   1.0000
  11.250   1.3814   0.02759   0.02132  -0.0324   0.0086   1.0000
  11.500   1.3829   0.02936   0.02323  -0.0302   0.0083   1.0000
  11.750   1.3833   0.03147   0.02548  -0.0284   0.0080   1.0000
  12.000   1.3831   0.03388   0.02802  -0.0272   0.0077   1.0000
  12.250   1.3825   0.03652   0.03080  -0.0264   0.0074   1.0000
  12.500   1.3808   0.03941   0.03384  -0.0259   0.0072   1.0000
  12.750   1.3782   0.04252   0.03708  -0.0256   0.0070   1.0000
  13.000   1.3743   0.04586   0.04055  -0.0254   0.0069   1.0000
  13.250   1.3691   0.04946   0.04427  -0.0254   0.0067   1.0000
  13.500   1.3625   0.05327   0.04821  -0.0255   0.0066   1.0000
  13.750   1.3542   0.05736   0.05243  -0.0256   0.0064   1.0000
  14.000   1.3461   0.06146   0.05668  -0.0258   0.0064   1.0000
  14.250   1.3355   0.06597   0.06134  -0.0260   0.0063   1.0000
  14.500   1.3247   0.07062   0.06615  -0.0264   0.0062   1.0000
  14.750   1.3119   0.07576   0.07147  -0.0270   0.0061   1.0000
  15.000   1.2981   0.08134   0.07724  -0.0282   0.0060   1.0000
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