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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.94 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe456-il-1000000.txt
Download as CSV file: xf-goe456-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3163   0.11113   0.10952  -0.0321   1.0000   0.0055
  -9.500  -0.3143   0.10859   0.10700  -0.0320   1.0000   0.0055
  -9.250  -0.3142   0.10607   0.10451  -0.0315   1.0000   0.0058
  -9.000  -0.3100   0.10318   0.10164  -0.0323   0.9997   0.0059
  -8.750  -0.2949   0.09904   0.09750  -0.0363   0.9985   0.0067
  -8.500  -0.2778   0.09474   0.09321  -0.0418   0.9964   0.0072
  -8.250  -0.2627   0.09087   0.08933  -0.0459   0.9936   0.0073
  -8.000  -0.2481   0.08706   0.08552  -0.0498   0.9900   0.0073
  -7.750  -0.2318   0.08278   0.08125  -0.0547   0.9859   0.0073
  -7.500  -0.2145   0.07825   0.07672  -0.0602   0.9816   0.0074
  -7.250  -0.1995   0.07433   0.07281  -0.0648   0.9737   0.0074
  -7.000  -0.1772   0.06617   0.06465  -0.0767   0.9695   0.0079
  -6.750  -0.1527   0.06282   0.06127  -0.0824   0.9620   0.0083
  -6.500  -0.1207   0.05845   0.05686  -0.0910   0.9563   0.0087
  -6.250  -0.0929   0.05438   0.05273  -0.0980   0.9448   0.0094
  -6.000  -0.0675   0.05006   0.04832  -0.1044   0.9316   0.0102
  -5.750  -0.0435   0.04562   0.04378  -0.1097   0.9183   0.0112
  -5.500  -0.0176   0.04210   0.04015  -0.1131   0.9069   0.0120
  -5.250   0.0062   0.03752   0.03544  -0.1168   0.8962   0.0121
  -5.000   0.0310   0.03119   0.02888  -0.1205   0.8865   0.0122
  -4.750   0.0536   0.02650   0.02384  -0.1225   0.8771   0.0122
  -4.500   0.0760   0.02305   0.02004  -0.1233   0.8689   0.0122
  -4.250   0.0990   0.02017   0.01678  -0.1234   0.8614   0.0122
  -4.000   0.1151   0.01103   0.00645  -0.1222   0.8533   0.0085
  -3.750   0.1415   0.01049   0.00577  -0.1219   0.8464   0.0094
  -3.500   0.1679   0.00987   0.00504  -0.1215   0.8388   0.0104
  -3.250   0.1943   0.00927   0.00430  -0.1211   0.8315   0.0110
  -3.000   0.2211   0.00888   0.00380  -0.1208   0.8236   0.0118
  -2.750   0.2478   0.00852   0.00334  -0.1205   0.8161   0.0125
  -2.500   0.2733   0.00754   0.00216  -0.1198   0.8079   0.0143
  -2.250   0.3002   0.00727   0.00183  -0.1196   0.7991   0.0168
  -2.000   0.3271   0.00710   0.00157  -0.1192   0.7900   0.0192
  -1.750   0.3537   0.00686   0.00125  -0.1189   0.7801   0.0269
  -1.500   0.3797   0.00643   0.00105  -0.1186   0.7697   0.1146
  -1.250   0.4064   0.00638   0.00102  -0.1183   0.7583   0.1412
  -1.000   0.4330   0.00637   0.00098  -0.1180   0.7446   0.1562
  -0.750   0.4592   0.00639   0.00092  -0.1176   0.7270   0.1663
  -0.500   0.4850   0.00641   0.00090  -0.1172   0.7071   0.1830
  -0.250   0.5108   0.00644   0.00088  -0.1168   0.6868   0.1964
   0.000   0.5365   0.00647   0.00088  -0.1164   0.6696   0.2184
   0.250   0.5626   0.00647   0.00090  -0.1160   0.6546   0.2518
   0.500   0.5886   0.00646   0.00093  -0.1157   0.6408   0.2954
   0.750   0.6144   0.00644   0.00098  -0.1154   0.6275   0.3488
   1.000   0.6388   0.00615   0.00107  -0.1149   0.6148   0.5288
   1.500   0.7029   0.00538   0.00124  -0.1170   0.5913   1.0000
   1.750   0.7292   0.00548   0.00129  -0.1167   0.5831   1.0000
   2.000   0.7553   0.00558   0.00135  -0.1164   0.5750   1.0000
   2.250   0.7817   0.00567   0.00141  -0.1161   0.5666   1.0000
   2.500   0.8078   0.00578   0.00150  -0.1158   0.5579   1.0000
   2.750   0.8330   0.00593   0.00157  -0.1153   0.5385   1.0000
   3.000   0.8583   0.00609   0.00166  -0.1148   0.5209   1.0000
   3.250   0.8828   0.00629   0.00177  -0.1142   0.4947   1.0000
   3.500   0.9068   0.00655   0.00191  -0.1135   0.4636   1.0000
   3.750   0.9272   0.00709   0.00214  -0.1122   0.3921   1.0000
   4.000   0.9384   0.00849   0.00276  -0.1094   0.2420   1.0000
   4.250   0.9529   0.00964   0.00332  -0.1073   0.1331   1.0000
   4.500   0.9663   0.01094   0.00414  -0.1048   0.0177   1.0000
   4.750   0.9899   0.01128   0.00451  -0.1040   0.0144   1.0000
   5.000   1.0113   0.01184   0.00523  -0.1027   0.0113   1.0000
   5.250   1.0348   0.01216   0.00557  -0.1020   0.0107   1.0000
   5.500   1.0571   0.01261   0.00606  -0.1010   0.0099   1.0000
   5.750   1.0786   0.01311   0.00663  -0.0998   0.0090   1.0000
   6.000   1.0989   0.01371   0.00729  -0.0984   0.0082   1.0000
   6.250   1.1175   0.01444   0.00808  -0.0968   0.0076   1.0000
   6.500   1.1330   0.01540   0.00913  -0.0946   0.0072   1.0000
   6.750   1.1408   0.01699   0.01081  -0.0912   0.0066   1.0000
   7.000   1.1480   0.01911   0.01300  -0.0877   0.0064   1.0000
   7.250   1.1701   0.01925   0.01320  -0.0867   0.0061   1.0000
   7.500   1.1879   0.02019   0.01420  -0.0850   0.0059   1.0000
   7.750   1.2063   0.02114   0.01521  -0.0835   0.0055   1.0000
   8.000   1.2253   0.02239   0.01653  -0.0820   0.0051   1.0000
   8.250   1.2485   0.02453   0.01877  -0.0812   0.0049   1.0000
   8.500   1.2915   0.03510   0.02962  -0.0839   0.0063   1.0000
   8.750   1.3066   0.03781   0.03254  -0.0820   0.0063   1.0000
   9.000   1.3185   0.04054   0.03550  -0.0797   0.0063   1.0000
   9.250   1.3278   0.04323   0.03842  -0.0772   0.0063   1.0000
   9.500   1.3337   0.04595   0.04137  -0.0743   0.0063   1.0000
   9.750   1.3365   0.04855   0.04421  -0.0711   0.0063   1.0000
  10.000   1.3363   0.05103   0.04691  -0.0677   0.0063   1.0000
  10.250   1.3329   0.05318   0.04928  -0.0640   0.0062   1.0000
  10.500   1.3256   0.05514   0.05143  -0.0598   0.0062   1.0000
  10.750   1.3296   0.05349   0.04986  -0.0557   0.0057   1.0000
  11.000   1.3239   0.05482   0.05134  -0.0518   0.0054   1.0000
  11.250   1.3121   0.05721   0.05390  -0.0483   0.0053   1.0000
  11.500   1.2994   0.06005   0.05691  -0.0455   0.0051   1.0000
  11.750   1.2848   0.06336   0.06038  -0.0433   0.0050   1.0000
  12.000   1.2699   0.06691   0.06408  -0.0419   0.0049   1.0000
  12.250   1.2532   0.07097   0.06829  -0.0412   0.0049   1.0000
  12.500   1.2346   0.07567   0.07314  -0.0413   0.0048   1.0000
  12.750   1.2157   0.08083   0.07845  -0.0423   0.0048   1.0000
  13.000   1.1952   0.08674   0.08450  -0.0442   0.0049   1.0000
  13.250   1.1753   0.09308   0.09097  -0.0470   0.0049   1.0000
  13.500   1.1550   0.10016   0.09818  -0.0507   0.0050   1.0000
  13.750   1.1343   0.10805   0.10619  -0.0553   0.0050   1.0000
  14.000   1.1136   0.11684   0.11510  -0.0609   0.0052   1.0000
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