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lrn1007 (lrn1007-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: lrn1007 (lrn1007-il)
Reynolds number: 200,000
Max Cl/Cd: 98.72 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lrn1007-il-200000-n5.txt
Download as CSV file: xf-lrn1007-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: lrn1007                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1044   0.09039   0.08623  -0.0788   0.8373   0.0048
  -8.250  -0.0971   0.08786   0.08373  -0.0799   0.8361   0.0056
  -8.000  -0.0919   0.08819   0.08413  -0.0828   0.8340   0.0072
  -7.750  -0.0858   0.08611   0.08208  -0.0839   0.8329   0.0072
  -7.500  -0.0783   0.08460   0.08061  -0.0871   0.8316   0.0073
  -7.250  -0.0663   0.08226   0.07827  -0.0901   0.8305   0.0073
  -7.000  -0.0592   0.07696   0.07300  -0.0872   0.8301   0.0076
  -6.750  -0.0484   0.07431   0.07035  -0.0891   0.8288   0.0077
  -6.500  -0.0365   0.07167   0.06771  -0.0913   0.8276   0.0079
  -6.250  -0.0223   0.06911   0.06512  -0.0940   0.8264   0.0079
  -6.000  -0.0066   0.06649   0.06250  -0.0969   0.8247   0.0079
  -5.750   0.0107   0.06381   0.05983  -0.1001   0.8228   0.0079
  -5.500   0.0504   0.06266   0.05853  -0.1094   0.8208   0.0073
  -5.250   0.0705   0.05981   0.05563  -0.1119   0.8195   0.0073
  -5.000   0.0923   0.05700   0.05276  -0.1144   0.8183   0.0073
  -4.750   0.1154   0.05427   0.04992  -0.1170   0.8171   0.0073
  -4.500   0.1375   0.05147   0.04704  -0.1191   0.8158   0.0072
  -4.250   0.1618   0.04882   0.04428  -0.1213   0.8146   0.0072
  -4.000   0.1866   0.04622   0.04158  -0.1233   0.8136   0.0072
  -3.750   0.2120   0.04369   0.03894  -0.1253   0.8127   0.0072
  -3.500   0.2386   0.04141   0.03655  -0.1272   0.8112   0.0072
  -3.250   0.2661   0.03930   0.03431  -0.1289   0.8095   0.0072
  -3.000   0.2934   0.03725   0.03212  -0.1303   0.8077   0.0072
  -2.750   0.3214   0.03537   0.03007  -0.1315   0.8059   0.0072
  -2.500   0.3493   0.03356   0.02810  -0.1324   0.8045   0.0072
  -2.250   0.3783   0.03203   0.02637  -0.1331   0.8032   0.0072
  -2.000   0.4023   0.02942   0.02363  -0.1345   0.8019   0.0081
  -1.750   0.4315   0.02834   0.02236  -0.1348   0.8008   0.0103
  -1.500   0.4630   0.02831   0.02205  -0.1343   0.7996   0.0113
  -1.250   0.4899   0.02755   0.02111  -0.1343   0.7965   0.0114
  -1.000   0.5169   0.02585   0.01921  -0.1344   0.7933   0.0118
  -0.750   0.5419   0.02330   0.01655  -0.1354   0.7908   0.0146
  -0.500   0.5703   0.02252   0.01556  -0.1352   0.7890   0.0183
  -0.250   0.6002   0.02237   0.01510  -0.1347   0.7875   0.0213
   1.000   0.7346   0.01780   0.00998  -0.1340   0.7741   0.0493
   1.250   0.7607   0.01751   0.00972  -0.1330   0.7699   0.0314
   1.500   0.7864   0.01712   0.00930  -0.1323   0.7657   0.0214
   1.750   0.8134   0.01634   0.00856  -0.1320   0.7628   0.0171
   2.000   0.8419   0.01577   0.00790  -0.1318   0.7605   0.0143
   2.250   0.8655   0.01570   0.00775  -0.1312   0.7544   0.0128
   2.500   0.8927   0.01546   0.00736  -0.1309   0.7503   0.0125
   2.750   0.9246   0.01362   0.00711  -0.1318   0.7478   1.0000
   3.000   0.9484   0.01374   0.00715  -0.1312   0.7413   1.0000
   3.250   0.9753   0.01360   0.00696  -0.1309   0.7363   1.0000
   3.500   1.0009   0.01354   0.00692  -0.1305   0.7305   1.0000
   3.750   1.0256   0.01351   0.00696  -0.1301   0.7236   1.0000
   4.000   1.0496   0.01351   0.00705  -0.1295   0.7159   1.0000
   4.250   1.0748   0.01338   0.00700  -0.1291   0.7081   1.0000
   4.750   1.1184   0.01353   0.00731  -0.1275   0.6805   1.0000
   5.000   1.1437   0.01328   0.00711  -0.1269   0.6646   1.0000
   5.250   1.1729   0.01275   0.00655  -0.1268   0.6464   1.0000
   5.500   1.2006   0.01239   0.00612  -0.1264   0.6197   1.0000
   5.750   1.2241   0.01240   0.00594  -0.1253   0.5751   1.0000
   6.000   1.2408   0.01293   0.00617  -0.1233   0.5211   1.0000
   6.250   1.2367   0.01456   0.00703  -0.1181   0.4087   1.0000
   6.500   1.2302   0.01625   0.00811  -0.1129   0.3164   1.0000
   6.750   1.2170   0.01816   0.00933  -0.1068   0.2178   1.0000
   7.000   1.2075   0.02031   0.01076  -0.1020   0.1179   1.0000
   7.250   1.1954   0.02310   0.01273  -0.0972   0.0103   1.0000
   7.500   1.2063   0.02431   0.01406  -0.0950   0.0061   1.0000
   7.750   1.2170   0.02561   0.01564  -0.0927   0.0049   1.0000
   8.000   1.2210   0.02753   0.01780  -0.0899   0.0023   1.0000
   8.250   1.2266   0.02938   0.01990  -0.0873   0.0020   1.0000
   8.500   1.2290   0.03153   0.02225  -0.0844   0.0019   1.0000
   8.750   1.2318   0.03381   0.02468  -0.0817   0.0018   1.0000
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