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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 100,000
Max Cl/Cd: 48.43 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe630-il-100000.txt
Download as CSV file: xf-goe630-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 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  -0.0307   0.10349   0.09896  -0.0807   0.9315   0.0792
  -8.000  -0.0155   0.10146   0.09692  -0.0879   0.9260   0.0824
  -7.750  -0.0297   0.10233   0.09782  -0.0902   0.9124   0.0832
  -7.500  -0.0052   0.09692   0.09240  -0.0956   0.9091   0.0844
  -7.250   0.0417   0.09035   0.08577  -0.0976   0.9090   0.0874
  -7.000   0.0409   0.08900   0.08444  -0.0959   0.8974   0.0896
  -6.750   0.0636   0.08602   0.08141  -0.1029   0.8925   0.0951
  -6.500   0.0531   0.08747   0.08283  -0.1108   0.8768   0.0972
  -6.250   0.0478   0.08566   0.08104  -0.1100   0.8648   0.0978
  -6.000   0.0783   0.07960   0.07501  -0.1067   0.8633   0.1000
  -5.750   0.1108   0.07570   0.07106  -0.1097   0.8601   0.1041
  -5.500   0.1078   0.07471   0.07008  -0.1082   0.8482   0.1067
  -5.250   0.1219   0.07482   0.06994  -0.1209   0.8354   0.1131
  -5.000   0.1358   0.07000   0.06524  -0.1168   0.8305   0.1148
  -4.750   0.1654   0.06647   0.06169  -0.1170   0.8271   0.1199
  -4.500   0.1704   0.06542   0.06061  -0.1171   0.8156   0.1257
  -4.250   0.2042   0.06166   0.05670  -0.1236   0.8106   0.1320
  -4.000   0.2094   0.06021   0.05527  -0.1207   0.8004   0.1351
  -3.750   0.2500   0.05729   0.05207  -0.1286   0.7945   0.1477
  -3.500   0.2683   0.05465   0.04948  -0.1270   0.7884   0.1515
  -3.250   0.2942   0.05296   0.04756  -0.1305   0.7788   0.1649
  -3.000   0.3253   0.04989   0.04449  -0.1309   0.7753   0.1738
  -2.750   0.3355   0.04871   0.04323  -0.1301   0.7634   0.1846
  -2.500   0.3733   0.04597   0.04034  -0.1329   0.7592   0.2018
  -2.250   0.3875   0.04499   0.03926  -0.1320   0.7480   0.2169
  -2.000   0.4209   0.04248   0.03667  -0.1333   0.7431   0.2357
  -1.750   0.4358   0.04134   0.03550  -0.1318   0.7329   0.2536
  -1.500   0.4668   0.03939   0.03343  -0.1325   0.7270   0.2866
  -1.000   0.5648   0.03265   0.02464  -0.1399   0.7118   0.1288
  -0.750   0.6045   0.02996   0.02171  -0.1415   0.7075   0.1224
  -0.500   0.6211   0.02923   0.02073  -0.1393   0.6959   0.1191
  -0.250   0.6616   0.02771   0.01885  -0.1405   0.6910   0.1216
   0.000   0.6785   0.02734   0.01833  -0.1384   0.6795   0.1221
   0.250   0.7188   0.02600   0.01666  -0.1395   0.6743   0.1241
   0.500   0.7359   0.02590   0.01643  -0.1373   0.6627   0.1281
   0.750   0.7749   0.02470   0.01514  -0.1385   0.6573   0.1369
   1.000   0.7915   0.02469   0.01512  -0.1364   0.6459   0.1433
   1.250   0.8294   0.02379   0.01416  -0.1374   0.6403   0.1610
   1.500   0.8466   0.02378   0.01422  -0.1354   0.6291   0.1798
   1.750   0.9024   0.02135   0.01339  -0.1404   0.6215   1.0000
   2.000   0.9262   0.02154   0.01334  -0.1394   0.6120   1.0000
   2.250   0.9520   0.02173   0.01331  -0.1388   0.6038   1.0000
   2.500   0.9776   0.02191   0.01332  -0.1382   0.5955   1.0000
   2.750   1.0025   0.02217   0.01343  -0.1375   0.5875   1.0000
   3.000   1.0279   0.02237   0.01349  -0.1369   0.5793   1.0000
   3.250   1.0528   0.02267   0.01366  -0.1363   0.5716   1.0000
   3.500   1.0766   0.02297   0.01387  -0.1356   0.5636   1.0000
   3.750   1.1048   0.02323   0.01397  -0.1355   0.5571   1.0000
   4.000   1.1231   0.02381   0.01455  -0.1341   0.5491   1.0000
   4.250   1.1571   0.02389   0.01444  -0.1349   0.5437   1.0000
   4.500   1.1693   0.02474   0.01536  -0.1326   0.5356   1.0000
   4.750   1.1979   0.02498   0.01548  -0.1327   0.5296   1.0000
   5.000   1.2193   0.02558   0.01607  -0.1318   0.5233   1.0000
   5.250   1.2377   0.02626   0.01676  -0.1304   0.5167   1.0000
   5.500   1.2695   0.02653   0.01691  -0.1311   0.5121   1.0000
   5.750   1.2828   0.02751   0.01799  -0.1291   0.5062   1.0000
   6.000   1.3008   0.02826   0.01878  -0.1278   0.5004   1.0000
   6.250   1.3328   0.02854   0.01896  -0.1285   0.4960   1.0000
   6.500   1.3451   0.02960   0.02011  -0.1264   0.4905   1.0000
   6.750   1.3574   0.03062   0.02123  -0.1244   0.4851   1.0000
   7.000   1.3851   0.03112   0.02171  -0.1245   0.4810   1.0000
   7.250   1.4154   0.03170   0.02223  -0.1252   0.4775   1.0000
   7.500   1.4054   0.03365   0.02444  -0.1201   0.4719   1.0000
   7.750   1.4203   0.03464   0.02551  -0.1186   0.4673   1.0000
   8.000   1.4544   0.03492   0.02575  -0.1197   0.4637   1.0000
   8.250   1.4640   0.03635   0.02728  -0.1175   0.4598   1.0000
   8.500   1.4318   0.03946   0.03065  -0.1101   0.4546   1.0000
   8.750   1.4396   0.04085   0.03211  -0.1079   0.4506   1.0000
   9.000   1.4830   0.04077   0.03204  -0.1101   0.4475   1.0000
   9.250   1.1829   0.06768   0.05934  -0.0883   0.4294   1.0000
   9.500   1.2393   0.06401   0.05570  -0.0880   0.4294   1.0000
   9.750   1.3052   0.05981   0.05152  -0.0886   0.4293   1.0000
  10.000   0.8251   0.12867   0.12085  -0.0990   0.4539   1.0000
  10.250   0.8437   0.13075   0.12294  -0.0990   0.4493   1.0000
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