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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.84 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe123-il-1000000-n5.txt
Download as CSV file: xf-goe123-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2989   0.09183   0.09001  -0.0309   0.9022   0.0064
  -8.000  -0.2928   0.08810   0.08626  -0.0332   0.8942   0.0067
  -7.750  -0.2878   0.08276   0.08090  -0.0377   0.8865   0.0072
  -7.500  -0.2725   0.08003   0.07814  -0.0409   0.8801   0.0074
  -7.000  -0.2378   0.07470   0.07275  -0.0477   0.8686   0.0079
  -6.750  -0.2186   0.07161   0.06963  -0.0517   0.8628   0.0084
  -6.500  -0.1971   0.06670   0.06467  -0.0581   0.8569   0.0092
  -6.250  -0.1724   0.06166   0.05957  -0.0649   0.8499   0.0099
  -6.000  -0.1485   0.05925   0.05710  -0.0683   0.8431   0.0101
  -5.750  -0.1233   0.05670   0.05450  -0.0719   0.8356   0.0105
  -5.500  -0.0965   0.05371   0.05144  -0.0760   0.8282   0.0113
  -5.250  -0.0603   0.04704   0.04463  -0.0847   0.8209   0.0128
  -5.000  -0.0334   0.04517   0.04268  -0.0872   0.8143   0.0131
  -4.750  -0.0055   0.04323   0.04069  -0.0897   0.8085   0.0135
  -4.500   0.0238   0.04097   0.03835  -0.0924   0.8026   0.0142
  -4.250   0.0675   0.03377   0.03086  -0.1000   0.7975   0.0163
  -4.000   0.0953   0.03239   0.02942  -0.1014   0.7916   0.0167
  -3.750   0.1223   0.03133   0.02828  -0.1025   0.7851   0.0170
  -3.500   0.1511   0.02979   0.02665  -0.1038   0.7772   0.0175
  -3.250   0.1817   0.02761   0.02431  -0.1055   0.7675   0.0180
  -3.000   0.2134   0.02506   0.02156  -0.1072   0.7558   0.0186
  -2.500   0.2845   0.01375   0.00918  -0.1115   0.7366   0.0210
  -2.250   0.3132   0.01229   0.00744  -0.1119   0.7267   0.0212
  -2.000   0.3414   0.01162   0.00664  -0.1122   0.7191   0.0215
  -1.750   0.3696   0.01105   0.00592  -0.1123   0.7103   0.0217
  -1.500   0.3980   0.01027   0.00495  -0.1125   0.7013   0.0218
  -1.250   0.4262   0.00977   0.00432  -0.1126   0.6921   0.0220
  -1.000   0.4544   0.00938   0.00383  -0.1126   0.6826   0.0223
  -0.750   0.4824   0.00907   0.00342  -0.1127   0.6717   0.0227
  -0.500   0.5102   0.00883   0.00307  -0.1126   0.6548   0.0231
  -0.250   0.5374   0.00870   0.00280  -0.1125   0.6276   0.0236
   0.000   0.5644   0.00864   0.00256  -0.1124   0.5934   0.0241
   0.250   0.5912   0.00863   0.00239  -0.1122   0.5591   0.0245
   0.500   0.6181   0.00863   0.00224  -0.1121   0.5293   0.0248
   0.750   0.6451   0.00865   0.00212  -0.1120   0.5016   0.0250
   1.000   0.6722   0.00866   0.00202  -0.1119   0.4778   0.0252
   1.250   0.6994   0.00868   0.00196  -0.1118   0.4561   0.0255
   1.500   0.7262   0.00879   0.00195  -0.1117   0.4298   0.0259
   1.750   0.7531   0.00890   0.00195  -0.1116   0.4038   0.0261
   2.000   0.7800   0.00898   0.00193  -0.1115   0.3801   0.0262
   2.250   0.8067   0.00911   0.00196  -0.1114   0.3563   0.0263
   2.500   0.8335   0.00923   0.00200  -0.1113   0.3352   0.0265
   2.750   0.8606   0.00930   0.00199  -0.1112   0.3209   0.0273
   3.000   0.8876   0.00938   0.00203  -0.1111   0.3091   0.0288
   3.250   0.9146   0.00949   0.00211  -0.1110   0.2980   0.0303
   3.500   0.9414   0.00964   0.00221  -0.1109   0.2848   0.0316
   3.750   0.9676   0.00985   0.00235  -0.1107   0.2665   0.0328
   4.000   0.9943   0.01001   0.00248  -0.1106   0.2541   0.0344
   4.250   1.0209   0.01016   0.00263  -0.1104   0.2429   0.0459
   4.500   1.0473   0.01029   0.00284  -0.1103   0.2305   0.1186
   4.750   1.0734   0.01050   0.00304  -0.1101   0.2163   0.1382
   5.000   1.0989   0.01077   0.00326  -0.1099   0.1970   0.1486
   5.250   1.1235   0.01115   0.00353  -0.1095   0.1717   0.1617
   5.500   1.1439   0.01032   0.00402  -0.1086   0.1475   1.0000
   5.750   1.1655   0.01110   0.00451  -0.1078   0.0941   1.0000
   6.000   1.1900   0.01150   0.00484  -0.1074   0.0814   1.0000
   6.250   1.2151   0.01180   0.00512  -0.1071   0.0745   1.0000
   6.500   1.2400   0.01213   0.00543  -0.1067   0.0669   1.0000
   6.750   1.2613   0.01288   0.00598  -0.1058   0.0337   1.0000
   7.000   1.2854   0.01328   0.00636  -0.1053   0.0272   1.0000
   7.250   1.3096   0.01363   0.00672  -0.1049   0.0236   1.0000
   7.500   1.3330   0.01407   0.00715  -0.1043   0.0186   1.0000
   7.750   1.3565   0.01447   0.00755  -0.1037   0.0158   1.0000
   8.000   1.3794   0.01493   0.00800  -0.1031   0.0130   1.0000
   8.250   1.4026   0.01532   0.00842  -0.1025   0.0118   1.0000
   8.500   1.4249   0.01579   0.00889  -0.1018   0.0103   1.0000
   8.750   1.4466   0.01631   0.00943  -0.1010   0.0090   1.0000
   9.000   1.4687   0.01675   0.00993  -0.1002   0.0085   1.0000
   9.250   1.4901   0.01724   0.01045  -0.0994   0.0079   1.0000
   9.500   1.5108   0.01777   0.01101  -0.0985   0.0073   1.0000
   9.750   1.5303   0.01838   0.01165  -0.0974   0.0067   1.0000
  10.000   1.5489   0.01904   0.01236  -0.0961   0.0062   1.0000
  10.250   1.5681   0.01959   0.01298  -0.0950   0.0059   1.0000
  10.500   1.5863   0.02019   0.01364  -0.0937   0.0055   1.0000
  10.750   1.6032   0.02084   0.01434  -0.0923   0.0052   1.0000
  11.000   1.6177   0.02151   0.01507  -0.0904   0.0050   1.0000
  11.250   1.6300   0.02226   0.01587  -0.0882   0.0047   1.0000
  11.500   1.6409   0.02313   0.01680  -0.0860   0.0045   1.0000
  11.750   1.6487   0.02424   0.01801  -0.0834   0.0043   1.0000
  12.000   1.6581   0.02527   0.01913  -0.0812   0.0042   1.0000
  12.250   1.6677   0.02633   0.02027  -0.0792   0.0041   1.0000
  12.500   1.6762   0.02749   0.02152  -0.0772   0.0040   1.0000
  12.750   1.6838   0.02878   0.02291  -0.0752   0.0039   1.0000
  13.000   1.6903   0.03020   0.02442  -0.0733   0.0038   1.0000
  13.250   1.6961   0.03174   0.02605  -0.0715   0.0036   1.0000
  13.500   1.7009   0.03341   0.02783  -0.0698   0.0035   1.0000
  13.750   1.7047   0.03524   0.02976  -0.0682   0.0035   1.0000
  14.000   1.7078   0.03721   0.03183  -0.0667   0.0034   1.0000
  14.250   1.7102   0.03931   0.03402  -0.0654   0.0033   1.0000
  14.500   1.7118   0.04158   0.03639  -0.0642   0.0032   1.0000
  14.750   1.7118   0.04410   0.03901  -0.0632   0.0031   1.0000
  15.000   1.7109   0.04679   0.04180  -0.0624   0.0030   1.0000
  15.250   1.7078   0.04987   0.04499  -0.0617   0.0030   1.0000
  15.500   1.7026   0.05333   0.04856  -0.0613   0.0029   1.0000
  15.750   1.6944   0.05736   0.05271  -0.0613   0.0028   1.0000
  16.000   1.6843   0.06190   0.05739  -0.0616   0.0028   1.0000
  16.250   1.6716   0.06705   0.06269  -0.0624   0.0027   1.0000
  16.500   1.6571   0.07271   0.06849  -0.0636   0.0027   1.0000
  16.750   1.6461   0.07804   0.07397  -0.0650   0.0027   1.0000
  17.000   1.6335   0.08378   0.07984  -0.0667   0.0027   1.0000
  17.250   1.6196   0.08980   0.08599  -0.0686   0.0026   1.0000
  17.500   1.6042   0.09623   0.09256  -0.0708   0.0026   1.0000
  17.750   1.5884   0.10288   0.09934  -0.0733   0.0026   1.0000
  18.000   1.5721   0.10968   0.10627  -0.0759   0.0026   1.0000
  18.250   1.5550   0.11674   0.11345  -0.0788   0.0026   1.0000
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