Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 50,000
Max Cl/Cd: 35.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe318-il-50000-n5.txt
Download as CSV file: xf-goe318-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4207   0.11969   0.11350   0.0067   1.0000   0.0939
  -9.000  -0.4226   0.11792   0.11182   0.0024   1.0000   0.0970
  -8.750  -0.4275   0.11651   0.11054  -0.0031   1.0000   0.0979
  -8.500  -0.4107   0.11024   0.10430  -0.0018   1.0000   0.0999
  -8.250  -0.3961   0.10583   0.09991  -0.0014   1.0000   0.1035
  -8.000  -0.3892   0.10264   0.09679  -0.0035   1.0000   0.1083
  -7.750  -0.3921   0.10085   0.09513  -0.0105   1.0000   0.1126
  -7.500  -0.3835   0.09660   0.09096  -0.0140   1.0000   0.1149
  -7.250  -0.3674   0.09240   0.08680  -0.0119   1.0000   0.1211
  -7.000  -0.3610   0.08998   0.08443  -0.0219   1.0000   0.1284
  -6.750  -0.3490   0.08556   0.08009  -0.0242   1.0000   0.1308
  -6.500  -0.3358   0.08185   0.07643  -0.0238   1.0000   0.1346
  -6.250  -0.3092   0.07845   0.07281  -0.0383   0.9514   0.1448
  -6.000  -0.2887   0.07355   0.06797  -0.0357   0.9351   0.1503
  -5.750  -0.2658   0.06980   0.06408  -0.0415   0.9167   0.1629
  -5.250  -0.1973   0.05865   0.05193  -0.0577   0.8874   0.0976
  -5.000  -0.1698   0.05369   0.04650  -0.0610   0.8750   0.0834
  -4.750  -0.1461   0.05051   0.04303  -0.0625   0.8634   0.0833
  -4.500  -0.1225   0.04753   0.03976  -0.0635   0.8528   0.0829
  -4.250  -0.0993   0.04473   0.03676  -0.0640   0.8431   0.0814
  -4.000  -0.0740   0.04209   0.03382  -0.0649   0.8327   0.0797
  -3.750  -0.0476   0.03964   0.03099  -0.0655   0.8235   0.0783
  -3.500  -0.0207   0.03742   0.02835  -0.0659   0.8147   0.0776
  -3.250   0.0069   0.03561   0.02610  -0.0664   0.8054   0.0794
  -3.000   0.0344   0.03397   0.02399  -0.0663   0.7977   0.0809
  -2.750   0.0625   0.03242   0.02208  -0.0665   0.7883   0.0809
  -2.500   0.0901   0.03104   0.02034  -0.0663   0.7806   0.0809
  -2.250   0.1181   0.02985   0.01881  -0.0662   0.7719   0.0812
  -2.000   0.1460   0.02883   0.01747  -0.0659   0.7641   0.0818
  -1.750   0.1739   0.02796   0.01632  -0.0656   0.7557   0.0828
  -1.500   0.2010   0.02721   0.01545  -0.0653   0.7477   0.0859
  -1.250   0.2278   0.02668   0.01482  -0.0648   0.7397   0.0906
  -1.000   0.2559   0.02621   0.01416  -0.0645   0.7314   0.0943
  -0.750   0.2832   0.02575   0.01348  -0.0638   0.7236   0.0971
  -0.500   0.3099   0.02536   0.01305  -0.0635   0.7149   0.1009
  -0.250   0.3361   0.02501   0.01262  -0.0628   0.7074   0.1069
   0.000   0.3630   0.02481   0.01237  -0.0627   0.6981   0.1163
   0.250   0.3890   0.02446   0.01205  -0.0619   0.6909   0.1401
   0.500   0.4126   0.02297   0.01197  -0.0620   0.6808   0.4342
   0.750   0.4440   0.02197   0.01160  -0.0612   0.6703   1.0000
   1.000   0.4691   0.02204   0.01133  -0.0598   0.6601   1.0000
   1.250   0.4944   0.02220   0.01127  -0.0591   0.6469   1.0000
   1.500   0.5197   0.02236   0.01124  -0.0583   0.6342   1.0000
   1.750   0.5451   0.02252   0.01122  -0.0575   0.6223   1.0000
   2.000   0.5706   0.02261   0.01113  -0.0566   0.6122   1.0000
   2.250   0.5964   0.02283   0.01126  -0.0561   0.6007   1.0000
   2.500   0.6221   0.02310   0.01146  -0.0557   0.5890   1.0000
   2.750   0.6478   0.02331   0.01159  -0.0551   0.5781   1.0000
   3.000   0.6736   0.02343   0.01162  -0.0543   0.5682   1.0000
   3.250   0.6991   0.02374   0.01191  -0.0540   0.5556   1.0000
   3.500   0.7246   0.02402   0.01219  -0.0536   0.5432   1.0000
   3.750   0.7501   0.02428   0.01244  -0.0531   0.5313   1.0000
   4.000   0.7757   0.02449   0.01262  -0.0525   0.5201   1.0000
   4.250   0.8012   0.02469   0.01281  -0.0519   0.5086   1.0000
   4.500   0.8263   0.02504   0.01321  -0.0515   0.4955   1.0000
   4.750   0.8512   0.02540   0.01358  -0.0510   0.4826   1.0000
   5.000   0.8762   0.02576   0.01397  -0.0506   0.4702   1.0000
   5.250   0.9011   0.02612   0.01435  -0.0500   0.4587   1.0000
   5.500   0.9265   0.02640   0.01460  -0.0494   0.4487   1.0000
   5.750   0.9506   0.02705   0.01534  -0.0491   0.4371   1.0000
   6.000   0.9749   0.02768   0.01604  -0.0487   0.4272   1.0000
   6.250   1.0001   0.02814   0.01653  -0.0482   0.4193   1.0000
   6.500   1.0232   0.02904   0.01758  -0.0480   0.4098   1.0000
   6.750   1.0484   0.02954   0.01810  -0.0475   0.4032   1.0000
   7.000   1.0704   0.03061   0.01940  -0.0473   0.3945   1.0000
   7.250   1.0957   0.03115   0.01999  -0.0468   0.3889   1.0000
   7.500   1.1163   0.03249   0.02160  -0.0467   0.3816   1.0000
   7.750   1.1399   0.03337   0.02264  -0.0464   0.3766   1.0000
   8.000   1.1626   0.03444   0.02392  -0.0461   0.3720   1.0000
   8.250   1.1811   0.03605   0.02584  -0.0459   0.3664   1.0000
   8.500   1.2036   0.03707   0.02706  -0.0455   0.3618   1.0000
   8.750   1.2247   0.03829   0.02852  -0.0451   0.3574   1.0000
   9.000   1.2378   0.04042   0.03101  -0.0449   0.3517   1.0000
   9.250   1.2604   0.04129   0.03214  -0.0443   0.3466   1.0000
   9.500   1.2721   0.04289   0.03404  -0.0435   0.3373   1.0000
   9.750   1.2914   0.04289   0.03421  -0.0421   0.3242   1.0000
  10.000   1.3086   0.04228   0.03368  -0.0402   0.3053   1.0000
  10.250   1.3160   0.04218   0.03359  -0.0380   0.2821   1.0000
  10.500   1.3131   0.04340   0.03488  -0.0362   0.2608   1.0000
  10.750   1.3062   0.04522   0.03680  -0.0345   0.2430   1.0000
  11.000   1.2978   0.04799   0.03972  -0.0341   0.2272   1.0000
  11.250   1.2886   0.05136   0.04326  -0.0343   0.2102   1.0000
  11.500   1.2750   0.05590   0.04809  -0.0354   0.1922   1.0000
  11.750   1.2570   0.06165   0.05419  -0.0373   0.1725   1.0000
  12.000   1.2448   0.06580   0.05803  -0.0381   0.1292   1.0000
  12.250   1.2274   0.07096   0.06279  -0.0392   0.1109   1.0000
  12.500   1.2092   0.07673   0.06841  -0.0407   0.1001   1.0000
  12.750   1.1919   0.08261   0.07422  -0.0423   0.0914   1.0000
  13.000   1.1772   0.08831   0.07992  -0.0438   0.0836   1.0000
  13.250   1.1635   0.09395   0.08547  -0.0454   0.0779   1.0000
  13.500   1.1544   0.09902   0.09058  -0.0468   0.0717   1.0000
<< Back to GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)

Polar data table (+)

Polar graphs


<< Back to GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)