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lrn1007 (lrn1007-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: lrn1007 (lrn1007-il)
Reynolds number: 50,000
Max Cl/Cd: 35.74 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lrn1007-il-50000-n5.txt
Download as CSV file: xf-lrn1007-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2482   0.11420   0.10776  -0.0513   0.9665   0.0355
  -8.000  -0.2489   0.11317   0.10677  -0.0518   0.9626   0.0360
  -7.750  -0.2509   0.11261   0.10625  -0.0526   0.9584   0.0364
  -7.500  -0.2448   0.11116   0.10483  -0.0555   0.9549   0.0367
  -7.250  -0.2404   0.11067   0.10434  -0.0589   0.9507   0.0370
  -7.000  -0.2345   0.10946   0.10314  -0.0617   0.9467   0.0371
  -6.750  -0.2306   0.10232   0.09608  -0.0565   0.9460   0.0386
  -6.500  -0.2234   0.09877   0.09253  -0.0562   0.9437   0.0405
  -6.250  -0.2123   0.09586   0.08963  -0.0583   0.9412   0.0421
  -6.000  -0.2112   0.09399   0.08778  -0.0582   0.9377   0.0435
  -5.750  -0.2050   0.09187   0.08568  -0.0594   0.9343   0.0453
  -5.500  -0.1911   0.08956   0.08335  -0.0628   0.9311   0.0475
  -5.250  -0.1653   0.08802   0.08171  -0.0706   0.9278   0.0498
  -5.000  -0.1474   0.08747   0.08103  -0.0758   0.9235   0.0504
  -4.750  -0.1476   0.08250   0.07621  -0.0724   0.9212   0.0519
  -4.500  -0.1379   0.07902   0.07273  -0.0720   0.9186   0.0549
  -4.250  -0.1143   0.07598   0.06950  -0.0760   0.9160   0.0589
  -4.000  -0.0795   0.07519   0.06843  -0.0838   0.9120   0.0637
  -3.750  -0.0703   0.07123   0.06455  -0.0834   0.9089   0.0657
  -3.500  -0.0533   0.06805   0.06134  -0.0844   0.9059   0.0712
  -3.000   0.0047   0.06260   0.05562  -0.0924   0.8998   0.0872
  -2.750   0.0282   0.05995   0.05287  -0.0948   0.8960   0.0959
  -2.500   0.0580   0.05734   0.05010  -0.0982   0.8928   0.1129
  -2.250   0.0909   0.05453   0.04714  -0.1023   0.8902   0.1413
  -1.750   0.1265   0.04937   0.04204  -0.1035   0.8828   0.2482
  -1.500   0.1559   0.04725   0.03982  -0.1055   0.8796   0.2856
  -1.250   0.1950   0.04504   0.03744  -0.1088   0.8771   0.3030
  -1.000   0.2362   0.04354   0.03554  -0.1126   0.8738   0.2933
  -0.750   0.2743   0.04244   0.03392  -0.1152   0.8693   0.2628
  -0.500   0.3230   0.04231   0.03301  -0.1177   0.8656   0.1824
  -0.250   0.3668   0.04213   0.03230  -0.1188   0.8626   0.1244
   0.000   0.3904   0.04231   0.03209  -0.1170   0.8564   0.0926
   0.250   0.4241   0.04161   0.03114  -0.1173   0.8523   0.0689
   0.500   0.4625   0.04166   0.03074  -0.1177   0.8489   0.0511
   0.750   0.4825   0.04076   0.02978  -0.1168   0.8424   0.0455
   1.000   0.5165   0.04076   0.02941  -0.1169   0.8379   0.0376
   1.250   0.5462   0.03996   0.02844  -0.1171   0.8329   0.0354
   1.500   0.5741   0.03968   0.02790  -0.1167   0.8269   0.0361
   1.750   0.6110   0.03922   0.02722  -0.1178   0.8231   0.0377
   2.000   0.6324   0.03905   0.02691  -0.1170   0.8154   0.0391
   2.250   0.6684   0.03883   0.02645  -0.1182   0.8107   0.0386
   2.500   0.6912   0.03899   0.02641  -0.1176   0.8026   0.0396
   2.750   0.7270   0.03894   0.02609  -0.1188   0.7973   0.0490
   3.000   0.7466   0.03764   0.02646  -0.1179   0.7889   1.0000
   3.250   0.7804   0.03798   0.02627  -0.1185   0.7834   1.0000
   3.500   0.7979   0.03858   0.02664  -0.1171   0.7731   1.0000
   3.750   0.8204   0.03905   0.02698  -0.1165   0.7640   1.0000
   4.000   0.8524   0.03926   0.02713  -0.1171   0.7571   1.0000
   4.250   0.8702   0.03975   0.02763  -0.1158   0.7459   1.0000
   4.500   0.8898   0.04017   0.02808  -0.1148   0.7349   1.0000
   4.750   0.9115   0.04047   0.02847  -0.1140   0.7244   1.0000
   5.000   0.9438   0.04034   0.02841  -0.1144   0.7166   1.0000
   5.250   0.9618   0.04062   0.02878  -0.1131   0.7040   1.0000
   5.500   0.9808   0.04080   0.02907  -0.1119   0.6910   1.0000
   5.750   1.0013   0.04087   0.02929  -0.1107   0.6779   1.0000
   6.000   1.0237   0.04081   0.02941  -0.1097   0.6649   1.0000
   6.250   1.0473   0.04064   0.02946  -0.1086   0.6517   1.0000
   6.500   1.0724   0.04031   0.02942  -0.1076   0.6383   1.0000
   6.750   1.0984   0.03981   0.02930  -0.1063   0.6242   1.0000
   7.000   1.1253   0.03914   0.02912  -0.1047   0.6094   1.0000
   7.250   1.1589   0.03243   0.02122  -0.0946   0.3924   1.0000
   7.500   1.1479   0.03515   0.02262  -0.0898   0.2431   1.0000
   7.750   1.1421   0.03812   0.02478  -0.0867   0.1325   1.0000
   8.000   1.1301   0.04234   0.02774  -0.0835   0.0172   1.0000
   8.250   1.1369   0.04478   0.03033  -0.0813   0.0116   1.0000
   8.500   1.1458   0.04695   0.03287  -0.0794   0.0093   1.0000
   8.750   1.1524   0.04941   0.03567  -0.0775   0.0079   1.0000
   9.000   1.1576   0.05200   0.03862  -0.0756   0.0076   1.0000
   9.250   1.1615   0.05474   0.04172  -0.0737   0.0075   1.0000
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