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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 100,000
Max Cl/Cd: 62 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe304-il-100000.txt
Download as CSV file: xf-goe304-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2964   0.11418   0.10950  -0.0261   1.0000   0.0622
  -8.000  -0.3184   0.11483   0.11026  -0.0226   1.0000   0.0624
  -7.750  -0.3406   0.11539   0.11094  -0.0195   1.0000   0.0625
  -7.500  -0.3576   0.11563   0.11127  -0.0190   1.0000   0.0626
  -7.250  -0.3544   0.11308   0.10877  -0.0219   0.9977   0.0629
  -7.000  -0.3359   0.10684   0.10252  -0.0181   0.9961   0.0638
  -6.750  -0.3119   0.10248   0.09814  -0.0213   0.9911   0.0653
  -6.500  -0.2859   0.09859   0.09423  -0.0270   0.9845   0.0673
  -6.250  -0.1605   0.08278   0.07860  -0.0481   0.9476   0.0744
  -6.000  -0.1368   0.07830   0.07411  -0.0509   0.9430   0.0765
  -5.750  -0.1261   0.07547   0.07128  -0.0529   0.9332   0.0785
  -5.500  -0.1013   0.07164   0.06739  -0.0597   0.9272   0.0820
  -5.250  -0.0752   0.07088   0.06642  -0.0755   0.9137   0.0846
  -5.000  -0.0952   0.07879   0.07396  -0.0775   0.9334   0.0844
  -4.750  -0.0750   0.07353   0.06877  -0.0783   0.9287   0.0855
  -4.250  -0.0323   0.06733   0.06259  -0.0803   0.9146   0.0915
  -4.000   0.0306   0.06351   0.05848  -0.0947   0.9102   0.0991
  -3.750   0.0397   0.06106   0.05609  -0.0927   0.8999   0.1009
  -3.500   0.0791   0.05797   0.05295  -0.0974   0.8955   0.1068
  -3.250   0.1193   0.05549   0.05022  -0.1044   0.8867   0.1140
  -3.000   0.1479   0.05259   0.04735  -0.1059   0.8811   0.1185
  -2.750   0.2039   0.04938   0.04392  -0.1143   0.8781   0.1304
  -2.500   0.2200   0.04790   0.04244  -0.1134   0.8677   0.1373
  -2.250   0.2650   0.04520   0.03962  -0.1184   0.8637   0.1520
  -2.000   0.3123   0.04260   0.03688  -0.1234   0.8608   0.1702
  -1.750   0.3315   0.04135   0.03557  -0.1232   0.8498   0.1837
  -1.500   0.3751   0.03923   0.03330  -0.1271   0.8459   0.2131
  -1.250   0.4013   0.03823   0.03221  -0.1277   0.8376   0.2450
   0.250   0.6346   0.02834   0.02044  -0.1373   0.7981   0.1379
   0.500   0.6763   0.02718   0.01878  -0.1381   0.7937   0.1268
   0.750   0.6989   0.02658   0.01813  -0.1371   0.7831   0.1241
   1.000   0.7354   0.02542   0.01679  -0.1376   0.7777   0.1210
   1.250   0.7597   0.02515   0.01643  -0.1366   0.7678   0.1208
   1.500   0.7933   0.02444   0.01560  -0.1366   0.7613   0.1257
   1.750   0.8181   0.02422   0.01536  -0.1357   0.7516   0.1284
   2.000   0.8493   0.02343   0.01463  -0.1354   0.7444   0.1345
   2.250   0.8740   0.02335   0.01454  -0.1344   0.7343   0.1449
   2.500   0.9070   0.02268   0.01385  -0.1342   0.7268   0.1607
   2.750   0.9317   0.02246   0.01377  -0.1332   0.7149   0.1990
   3.000   0.9641   0.02053   0.01298  -0.1325   0.7065   1.0000
   3.250   0.9895   0.02056   0.01284  -0.1314   0.6942   1.0000
   3.500   1.0141   0.02071   0.01289  -0.1303   0.6824   1.0000
   3.750   1.0461   0.02048   0.01250  -0.1301   0.6738   1.0000
   4.000   1.0689   0.02075   0.01274  -0.1289   0.6613   1.0000
   4.250   1.0936   0.02095   0.01291  -0.1280   0.6499   1.0000
   4.500   1.1249   0.02080   0.01263  -0.1278   0.6408   1.0000
   4.750   1.1469   0.02110   0.01295  -0.1265   0.6276   1.0000
   5.000   1.1712   0.02130   0.01314  -0.1255   0.6153   1.0000
   5.250   1.1984   0.02133   0.01312  -0.1249   0.6036   1.0000
   5.500   1.2256   0.02130   0.01301  -0.1241   0.5909   1.0000
   5.750   1.2485   0.02140   0.01311  -0.1228   0.5756   1.0000
   6.000   1.2718   0.02147   0.01316  -0.1215   0.5598   1.0000
   6.250   1.2949   0.02154   0.01322  -0.1202   0.5435   1.0000
   6.500   1.3177   0.02167   0.01334  -0.1190   0.5271   1.0000
   6.750   1.3401   0.02182   0.01345  -0.1176   0.5100   1.0000
   7.000   1.3621   0.02198   0.01356  -0.1162   0.4917   1.0000
   7.250   1.3814   0.02228   0.01384  -0.1145   0.4718   1.0000
   7.500   1.3998   0.02266   0.01420  -0.1126   0.4508   1.0000
   7.750   1.4183   0.02310   0.01458  -0.1108   0.4301   1.0000
   8.000   1.4369   0.02363   0.01500  -0.1091   0.4100   1.0000
   8.250   1.4530   0.02429   0.01561  -0.1071   0.3894   1.0000
   8.500   1.4683   0.02500   0.01630  -0.1050   0.3695   1.0000
   8.750   1.4836   0.02577   0.01701  -0.1030   0.3511   1.0000
   9.000   1.4985   0.02659   0.01780  -0.1010   0.3339   1.0000
   9.250   1.5129   0.02748   0.01864  -0.0989   0.3178   1.0000
   9.500   1.5266   0.02842   0.01954  -0.0969   0.3024   1.0000
   9.750   1.5399   0.02943   0.02052  -0.0947   0.2876   1.0000
  10.000   1.5527   0.03053   0.02159  -0.0926   0.2734   1.0000
  10.250   1.5650   0.03169   0.02270  -0.0905   0.2596   1.0000
  10.500   1.5781   0.03291   0.02384  -0.0885   0.2465   1.0000
  10.750   1.5917   0.03417   0.02503  -0.0866   0.2342   1.0000
  11.000   1.5996   0.03552   0.02649  -0.0840   0.2234   1.0000
  11.250   1.6120   0.03688   0.02786  -0.0821   0.2134   1.0000
  11.500   1.6230   0.03806   0.02897  -0.0802   0.2037   1.0000
  11.750   1.6241   0.03948   0.03057  -0.0770   0.1955   1.0000
  12.000   1.6391   0.04069   0.03161  -0.0758   0.1868   1.0000
  12.250   1.6362   0.04227   0.03350  -0.0724   0.1806   1.0000
  12.500   1.6484   0.04350   0.03469  -0.0709   0.1735   1.0000
  12.750   1.6490   0.04528   0.03670  -0.0683   0.1677   1.0000
  13.000   1.6517   0.04683   0.03835  -0.0661   0.1615   1.0000
  13.250   1.6579   0.04848   0.04003  -0.0644   0.1554   1.0000
  13.500   1.6521   0.05059   0.04239  -0.0619   0.1498   1.0000
  13.750   1.6611   0.05202   0.04370  -0.0605   0.1429   1.0000
  14.000   1.6480   0.05483   0.04688  -0.0581   0.1380   1.0000
  14.250   1.6472   0.05680   0.04885  -0.0566   0.1316   1.0000
  14.500   1.6380   0.05981   0.05207  -0.0549   0.1259   1.0000
  14.750   1.6314   0.06249   0.05482  -0.0537   0.1195   1.0000
  15.000   1.6235   0.06572   0.05817  -0.0525   0.1135   1.0000
  15.250   1.6149   0.06896   0.06150  -0.0517   0.1075   1.0000
  15.500   1.6087   0.07232   0.06492  -0.0509   0.1017   1.0000
  15.750   1.5975   0.07625   0.06902  -0.0505   0.0968   1.0000
  16.000   1.6009   0.07883   0.07150  -0.0496   0.0911   1.0000
  16.250   1.5833   0.08393   0.07693  -0.0499   0.0881   1.0000
  16.500   1.5781   0.08752   0.08060  -0.0499   0.0842   1.0000
  16.750   1.5822   0.09024   0.08327  -0.0492   0.0800   1.0000
  17.000   1.5611   0.09622   0.08959  -0.0505   0.0784   1.0000
  17.250   1.5417   0.10231   0.09597  -0.0522   0.0768   1.0000
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