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GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 405 AIRFOIL (goe405-il)
Reynolds number: 50,000
Max Cl/Cd: 29.21 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe405-il-50000-n5.txt
Download as CSV file: xf-goe405-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 405 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2455   0.12141   0.11539  -0.0489   0.9730   0.1017
  -8.250  -0.2427   0.11932   0.11334  -0.0531   0.9652   0.1021
  -8.000  -0.2389   0.11674   0.11081  -0.0571   0.9574   0.1023
  -7.750  -0.2120   0.10996   0.10397  -0.0563   0.9543   0.1038
  -7.500  -0.1945   0.10603   0.09999  -0.0571   0.9490   0.1075
  -7.250  -0.1879   0.10341   0.09738  -0.0587   0.9413   0.1103
  -7.000  -0.1890   0.10168   0.09568  -0.0624   0.9318   0.1152
  -6.000  -0.1612   0.08448   0.07835  -0.0746   0.8987   0.0707
  -5.750  -0.1442   0.08033   0.07414  -0.0791   0.8927   0.0700
  -5.500  -0.1379   0.07716   0.07091  -0.0812   0.8835   0.0710
  -5.250  -0.1164   0.07262   0.06622  -0.0867   0.8777   0.0718
  -5.000  -0.1053   0.06919   0.06269  -0.0886   0.8694   0.0717
  -4.750  -0.0817   0.06477   0.05808  -0.0929   0.8636   0.0713
  -4.500  -0.0597   0.06026   0.05329  -0.0969   0.8569   0.0726
  -4.250  -0.0361   0.05617   0.04890  -0.1002   0.8502   0.0754
  -4.000  -0.0037   0.05296   0.04541  -0.1034   0.8463   0.0772
  -3.750   0.0123   0.05026   0.04244  -0.1037   0.8376   0.0781
  -3.500   0.0456   0.04722   0.03898  -0.1066   0.8328   0.0822
  -3.250   0.0764   0.04358   0.03465  -0.1090   0.8272   0.0866
  -3.000   0.1031   0.04094   0.03145  -0.1098   0.8203   0.0886
  -2.750   0.1393   0.03933   0.02955  -0.1116   0.8161   0.0923
  -2.500   0.1589   0.03834   0.02826  -0.1107   0.8073   0.0967
  -2.250   0.1939   0.03701   0.02656  -0.1120   0.8024   0.1057
  -2.000   0.2193   0.03621   0.02547  -0.1117   0.7948   0.1130
  -1.750   0.2508   0.03526   0.02426  -0.1123   0.7887   0.1221
  -1.500   0.2896   0.03443   0.02322  -0.1138   0.7851   0.1401
  -1.250   0.3053   0.03452   0.02320  -0.1119   0.7748   0.1566
  -1.000   0.3438   0.03402   0.02251  -0.1134   0.7709   0.1861
  -0.750   0.3609   0.03429   0.02260  -0.1118   0.7609   0.2096
  -0.500   0.3990   0.03370   0.02190  -0.1133   0.7566   0.2357
  -0.250   0.4185   0.03381   0.02186  -0.1121   0.7471   0.2529
   0.000   0.4559   0.03321   0.02111  -0.1133   0.7424   0.2717
   0.250   0.4771   0.03326   0.02110  -0.1123   0.7335   0.2873
   0.500   0.5112   0.03276   0.02054  -0.1131   0.7279   0.3052
   1.000   0.5650   0.03236   0.02017  -0.1127   0.7131   0.3484
   1.250   0.6061   0.03142   0.01948  -0.1146   0.7096   0.3984
   1.500   0.6244   0.03071   0.02000  -0.1133   0.6985   1.0000
   1.750   0.6656   0.03039   0.01934  -0.1148   0.6945   1.0000
   2.000   0.6763   0.03115   0.01995  -0.1123   0.6826   1.0000
   2.500   0.7262   0.03164   0.02011  -0.1111   0.6667   1.0000
   2.750   0.7445   0.03215   0.02051  -0.1096   0.6570   1.0000
   3.000   0.7758   0.03210   0.02034  -0.1098   0.6505   1.0000
   3.250   0.7897   0.03282   0.02101  -0.1079   0.6400   1.0000
   3.500   0.8247   0.03258   0.02066  -0.1085   0.6344   1.0000
   3.750   0.8353   0.03346   0.02151  -0.1062   0.6232   1.0000
   4.000   0.8732   0.03307   0.02106  -0.1071   0.6183   1.0000
   4.250   0.8809   0.03410   0.02207  -0.1045   0.6066   1.0000
   4.500   0.9216   0.03355   0.02147  -0.1058   0.6022   1.0000
   4.750   0.9264   0.03473   0.02268  -0.1028   0.5903   1.0000
   5.250   0.9722   0.03533   0.02328  -0.1012   0.5741   1.0000
   5.750   1.0184   0.03589   0.02389  -0.0996   0.5579   1.0000
   6.000   1.0231   0.03722   0.02528  -0.0969   0.5468   1.0000
   6.250   1.0646   0.03645   0.02451  -0.0980   0.5419   1.0000
   6.500   1.0653   0.03803   0.02619  -0.0949   0.5303   1.0000
   6.750   1.0818   0.03873   0.02695  -0.0936   0.5216   1.0000
   7.000   1.1069   0.03891   0.02719  -0.0930   0.5141   1.0000
   7.250   1.1146   0.04021   0.02857  -0.0909   0.5043   1.0000
   7.500   1.1478   0.03987   0.02832  -0.0910   0.4980   1.0000
   7.750   1.1488   0.04167   0.03023  -0.0884   0.4877   1.0000
   8.000   1.1872   0.04100   0.02965  -0.0889   0.4821   1.0000
   8.250   1.1816   0.04330   0.03207  -0.0859   0.4715   1.0000
   8.500   1.2233   0.04243   0.03134  -0.0867   0.4663   1.0000
   8.750   1.2115   0.04524   0.03428  -0.0833   0.4555   1.0000
   9.000   1.2563   0.04416   0.03332  -0.0842   0.4507   1.0000
   9.250   1.2364   0.04767   0.03698  -0.0806   0.4397   1.0000
   9.500   1.2835   0.04638   0.03584  -0.0815   0.4352   1.0000
   9.750   1.2549   0.05075   0.04035  -0.0777   0.4239   1.0000
  10.000   1.3020   0.04937   0.03920  -0.0784   0.4198   1.0000
  10.250   1.2630   0.05498   0.04494  -0.0746   0.4083   1.0000
  10.500   1.3075   0.05364   0.04381  -0.0749   0.4047   1.0000
  10.750   1.2590   0.06073   0.05099  -0.0717   0.3924   1.0000
  11.000   1.3040   0.05897   0.04949  -0.0716   0.3893   1.0000
  11.250   1.2460   0.06798   0.05853  -0.0695   0.3761   1.0000
  11.500   1.1976   0.07740   0.06798  -0.0694   0.3631   1.0000
  11.750   1.2217   0.07753   0.06834  -0.0685   0.3599   1.0000
  12.250   1.2367   0.08054   0.07169  -0.0664   0.3420   1.0000
  12.500   1.1514   0.09887   0.08989  -0.0708   0.3312   1.0000
  12.750   1.1341   0.10555   0.09666  -0.0720   0.3239   1.0000
  13.000   1.1298   0.10996   0.10120  -0.0726   0.3172   1.0000
  13.250   1.2205   0.09189   0.08364  -0.0640   0.2919   1.0000
  13.500   1.1737   0.10581   0.09758  -0.0683   0.2917   1.0000
  14.000   1.2288   0.09586   0.08797  -0.0619   0.2212   1.0000
  14.250   1.2180   0.10074   0.09294  -0.0629   0.1951   1.0000
  14.500   1.2020   0.10716   0.09952  -0.0647   0.1728   1.0000
  14.750   1.1896   0.11071   0.10161  -0.0646   0.0751   1.0000
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