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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.79 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe427-il-1000000.txt
Download as CSV file: xf-goe427-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 427 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3546   0.10170   0.10011  -0.0208   1.0000   0.0067
  -8.500  -0.3559   0.09956   0.09800  -0.0198   1.0000   0.0067
  -8.250  -0.3597   0.09753   0.09599  -0.0185   1.0000   0.0067
  -8.000  -0.3549   0.09291   0.09139  -0.0208   0.9990   0.0069
  -7.750  -0.3395   0.08996   0.08844  -0.0236   0.9974   0.0073
  -7.500  -0.3212   0.08637   0.08484  -0.0285   0.9951   0.0075
  -7.250  -0.2997   0.08271   0.08118  -0.0338   0.9924   0.0083
  -7.000  -0.2768   0.07857   0.07703  -0.0399   0.9893   0.0089
  -6.750  -0.2450   0.07416   0.07260  -0.0486   0.9866   0.0099
  -6.500  -0.2111   0.06979   0.06821  -0.0577   0.9847   0.0100
  -6.250  -0.1776   0.06517   0.06356  -0.0658   0.9834   0.0101
  -6.000  -0.1520   0.06118   0.05953  -0.0710   0.9788   0.0101
  -5.750  -0.1193   0.05665   0.05497  -0.0777   0.9758   0.0101
  -4.000   0.1222   0.02606   0.02361  -0.1132   0.9476   0.0137
  -3.750   0.1508   0.01165   0.00782  -0.1149   0.9389   0.0127
  -3.500   0.1769   0.01018   0.00601  -0.1144   0.9315   0.0141
  -3.250   0.2043   0.00984   0.00556  -0.1141   0.9240   0.0148
  -3.000   0.2308   0.00853   0.00399  -0.1138   0.9150   0.0169
  -2.750   0.2577   0.00854   0.00395  -0.1135   0.9022   0.0187
  -2.500   0.2848   0.00858   0.00393  -0.1131   0.8871   0.0206
  -2.250   0.3105   0.00780   0.00296  -0.1125   0.8713   0.0226
  -2.000   0.3368   0.00757   0.00266  -0.1121   0.8562   0.0251
  -1.750   0.3632   0.00752   0.00254  -0.1117   0.8409   0.0276
  -1.500   0.3895   0.00740   0.00233  -0.1112   0.8260   0.0296
  -1.250   0.4158   0.00738   0.00223  -0.1107   0.8114   0.0308
  -1.000   0.4410   0.00689   0.00163  -0.1101   0.7970   0.0334
  -0.750   0.4665   0.00671   0.00136  -0.1096   0.7813   0.0352
  -0.500   0.4917   0.00664   0.00118  -0.1089   0.7617   0.0363
  -0.250   0.5162   0.00663   0.00104  -0.1080   0.7326   0.0376
   0.000   0.5409   0.00665   0.00094  -0.1073   0.7053   0.0400
   0.250   0.5664   0.00666   0.00085  -0.1067   0.6817   0.0426
   0.500   0.5911   0.00674   0.00080  -0.1060   0.6499   0.0451
   0.750   0.6148   0.00688   0.00076  -0.1051   0.6016   0.0545
   1.000   0.6379   0.00700   0.00086  -0.1042   0.5562   0.1257
   1.250   0.6621   0.00707   0.00097  -0.1036   0.5275   0.2028
   1.750   0.7220   0.00588   0.00131  -0.1053   0.4846   1.0000
   2.000   0.7468   0.00609   0.00138  -0.1047   0.4573   1.0000
   2.250   0.7709   0.00635   0.00147  -0.1039   0.4188   1.0000
   2.500   0.7935   0.00676   0.00162  -0.1030   0.3617   1.0000
   2.750   0.8150   0.00730   0.00183  -0.1019   0.2973   1.0000
   3.000   0.8345   0.00810   0.00216  -0.1005   0.1987   1.0000
   3.250   0.8527   0.00908   0.00263  -0.0990   0.0889   1.0000
   3.500   0.8756   0.00957   0.00292  -0.0981   0.0460   1.0000
   3.750   0.9005   0.00981   0.00312  -0.0976   0.0382   1.0000
   4.000   0.9256   0.01002   0.00336  -0.0971   0.0356   1.0000
   4.250   0.9504   0.01028   0.00366  -0.0965   0.0336   1.0000
   4.500   0.9746   0.01060   0.00400  -0.0958   0.0311   1.0000
   4.750   0.9985   0.01096   0.00439  -0.0951   0.0288   1.0000
   5.000   1.0215   0.01143   0.00495  -0.0942   0.0265   1.0000
   5.250   1.0450   0.01180   0.00537  -0.0934   0.0251   1.0000
   5.500   1.0696   0.01202   0.00560  -0.0929   0.0241   1.0000
   5.750   1.0938   0.01230   0.00591  -0.0923   0.0221   1.0000
   6.000   1.1177   0.01259   0.00619  -0.0917   0.0195   1.0000
   6.250   1.1369   0.01342   0.00711  -0.0903   0.0164   1.0000
   6.500   1.1623   0.01352   0.00721  -0.0899   0.0152   1.0000
   6.750   1.1863   0.01377   0.00747  -0.0893   0.0135   1.0000
   7.000   1.2080   0.01427   0.00796  -0.0883   0.0116   1.0000
   7.250   1.2267   0.01509   0.00888  -0.0868   0.0104   1.0000
   7.500   1.2493   0.01544   0.00928  -0.0860   0.0096   1.0000
   7.750   1.2708   0.01592   0.00979  -0.0850   0.0087   1.0000
   8.000   1.2911   0.01648   0.01039  -0.0839   0.0080   1.0000
   8.250   1.3044   0.01777   0.01180  -0.0815   0.0072   1.0000
   8.500   1.3134   0.01960   0.01382  -0.0784   0.0068   1.0000
   8.750   1.3311   0.02044   0.01476  -0.0768   0.0066   1.0000
   9.000   1.3480   0.02136   0.01578  -0.0752   0.0063   1.0000
   9.250   1.3643   0.02233   0.01687  -0.0734   0.0059   1.0000
   9.500   1.3803   0.02326   0.01790  -0.0718   0.0055   1.0000
   9.750   1.3966   0.02399   0.01871  -0.0702   0.0052   1.0000
  10.000   1.4107   0.02478   0.01957  -0.0683   0.0049   1.0000
  10.250   1.4208   0.02584   0.02074  -0.0657   0.0047   1.0000
  10.500   1.4262   0.02756   0.02262  -0.0625   0.0045   1.0000
  10.750   1.4257   0.03023   0.02555  -0.0587   0.0044   1.0000
  11.000   1.4199   0.03361   0.02925  -0.0546   0.0043   1.0000
  11.250   1.4047   0.03795   0.03397  -0.0499   0.0042   1.0000
  11.500   1.3821   0.04277   0.03917  -0.0454   0.0041   1.0000
  11.750   1.3733   0.04570   0.04230  -0.0427   0.0042   1.0000
  12.000   1.3469   0.05101   0.04791  -0.0400   0.0041   1.0000
  12.250   1.3329   0.05496   0.05206  -0.0388   0.0041   1.0000
  13.250   1.1850   0.07455   0.07232  -0.0423   0.0043   1.0000
  13.500   1.1637   0.08256   0.08049  -0.0457   0.0043   1.0000
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