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

NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NLR-7301 AIRFOIL (nlr7301-il)
Reynolds number: 100,000
Max Cl/Cd: 26.72 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlr7301-il-100000-n5.txt
Download as CSV file: xf-nlr7301-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7301 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.8017   0.08033   0.07296  -0.0637   1.0000   0.0570
 -14.250  -0.8432   0.07181   0.06411  -0.0681   1.0000   0.0571
 -14.000  -0.8706   0.06582   0.05782  -0.0705   1.0000   0.0574
 -13.750  -0.8909   0.06102   0.05272  -0.0718   1.0000   0.0578
 -13.500  -0.9064   0.05695   0.04835  -0.0724   1.0000   0.0582
 -13.250  -0.9114   0.05399   0.04519  -0.0724   1.0000   0.0587
 -13.000  -0.9039   0.05220   0.04339  -0.0721   1.0000   0.0593
 -12.750  -0.8977   0.05044   0.04158  -0.0717   1.0000   0.0600
 -12.500  -0.8930   0.04866   0.03973  -0.0711   1.0000   0.0608
 -12.250  -0.8899   0.04687   0.03783  -0.0703   1.0000   0.0617
 -12.000  -0.8882   0.04511   0.03593  -0.0690   1.0000   0.0627
 -11.750  -0.8890   0.04347   0.03409  -0.0671   1.0000   0.0638
 -11.500  -0.8895   0.04223   0.03276  -0.0646   1.0000   0.0646
 -11.250  -0.8880   0.04145   0.03202  -0.0617   1.0000   0.0653
 -11.000  -0.8917   0.04076   0.03133  -0.0581   1.0000   0.0660
 -10.750  -0.8986   0.04012   0.03068  -0.0539   1.0000   0.0666
 -10.500  -0.9060   0.03946   0.02998  -0.0496   1.0000   0.0673
 -10.250  -0.8917   0.03834   0.02875  -0.0488   0.9973   0.0687
 -10.000  -0.8674   0.03702   0.02723  -0.0498   0.9935   0.0707
  -9.750  -0.8426   0.03608   0.02637  -0.0505   0.9898   0.0723
  -9.500  -0.8185   0.03512   0.02537  -0.0512   0.9857   0.0743
  -9.250  -0.7920   0.03411   0.02423  -0.0520   0.9823   0.0768
  -9.000  -0.7633   0.03320   0.02337  -0.0531   0.9796   0.0789
  -8.750  -0.7410   0.03240   0.02258  -0.0532   0.9746   0.0813
  -8.500  -0.7147   0.03159   0.02166  -0.0538   0.9706   0.0846
  -8.250  -0.6873   0.03079   0.02096  -0.0548   0.9675   0.0874
  -8.000  -0.6590   0.03006   0.02020  -0.0557   0.9650   0.0911
  -7.750  -0.6413   0.02943   0.01960  -0.0548   0.9596   0.0942
  -7.500  -0.6178   0.02877   0.01899  -0.0550   0.9557   0.0982
  -7.250  -0.5907   0.02811   0.01833  -0.0557   0.9527   0.1030
  -7.000  -0.5611   0.02745   0.01771  -0.0569   0.9502   0.1086
  -6.750  -0.5445   0.02692   0.01723  -0.0558   0.9445   0.1136
  -6.500  -0.5233   0.02640   0.01673  -0.0554   0.9400   0.1201
  -6.250  -0.4989   0.02580   0.01622  -0.0557   0.9367   0.1276
  -6.000  -0.4716   0.02523   0.01572  -0.0565   0.9341   0.1372
  -5.750  -0.4428   0.02464   0.01522  -0.0576   0.9319   0.1494
  -5.500  -0.4324   0.02425   0.01489  -0.0552   0.9249   0.1607
  -5.250  -0.4102   0.02364   0.01444  -0.0552   0.9206   0.1792
  -5.000  -0.3849   0.02295   0.01396  -0.0559   0.9175   0.2089
  -4.750  -0.3581   0.02202   0.01338  -0.0572   0.9150   0.2619
  -4.500  -0.3299   0.02087   0.01288  -0.0591   0.9128   0.3602
  -4.250  -0.3183   0.02090   0.01356  -0.0559   0.9068   0.4518
  -4.000  -0.2957   0.02133   0.01419  -0.0543   0.9025   0.5107
  -3.750  -0.2668   0.02153   0.01436  -0.0545   0.8995   0.5442
  -3.500  -0.2363   0.02186   0.01466  -0.0547   0.8967   0.5664
  -3.250  -0.2035   0.02213   0.01488  -0.0554   0.8943   0.5846
  -3.000  -0.1708   0.02253   0.01525  -0.0557   0.8923   0.5988
  -2.750  -0.1561   0.02301   0.01575  -0.0530   0.8865   0.6082
  -2.500  -0.1333   0.02338   0.01610  -0.0519   0.8816   0.6195
  -2.250  -0.1088   0.02410   0.01686  -0.0501   0.8778   0.6308
  -2.000  -0.0800   0.02475   0.01751  -0.0494   0.8747   0.6472
  -1.750  -0.0538   0.02568   0.01852  -0.0469   0.8721   0.6560
  -1.500  -0.0164   0.02557   0.01833  -0.0493   0.8701   0.6674
  -1.250  -0.0106   0.02597   0.01878  -0.0450   0.8610   0.6705
  -1.000   0.0154   0.02611   0.01895  -0.0443   0.8564   0.6739
  -0.750   0.0471   0.02611   0.01895  -0.0447   0.8527   0.6778
  -0.500   0.0832   0.02595   0.01878  -0.0462   0.8499   0.6823
  -0.250   0.1107   0.02574   0.01855  -0.0471   0.8431   0.6881
   0.000   0.1423   0.02532   0.01814  -0.0472   0.8327   0.6912
   0.250   0.1807   0.02442   0.01724  -0.0470   0.8173   0.6933
   0.500   0.2187   0.02321   0.01600  -0.0463   0.7958   0.6956
   0.750   0.2508   0.02238   0.01515  -0.0455   0.7762   0.6981
   1.000   0.2816   0.02181   0.01459  -0.0452   0.7603   0.7012
   1.250   0.3055   0.02150   0.01430  -0.0442   0.7410   0.7051
   1.500   0.3344   0.02104   0.01382  -0.0442   0.7172   0.7091
   1.750   0.3595   0.02067   0.01344  -0.0438   0.6811   0.7127
   2.000   0.3921   0.02009   0.01259  -0.0429   0.5967   0.7145
   2.250   0.4110   0.02064   0.01205  -0.0400   0.4219   0.7166
   2.500   0.4208   0.02171   0.01241  -0.0371   0.2976   0.7194
   2.750   0.4375   0.02251   0.01274  -0.0356   0.2237   0.7225
   3.000   0.4590   0.02308   0.01300  -0.0350   0.1851   0.7255
   3.250   0.4828   0.02355   0.01326  -0.0347   0.1626   0.7288
   3.500   0.5083   0.02397   0.01352  -0.0349   0.1474   0.7323
   3.750   0.5333   0.02436   0.01382  -0.0349   0.1361   0.7355
   4.000   0.5544   0.02479   0.01420  -0.0336   0.1277   0.7379
   4.250   0.5754   0.02527   0.01460  -0.0326   0.1209   0.7405
   4.500   0.5982   0.02569   0.01503  -0.0318   0.1145   0.7434
   4.750   0.6211   0.02620   0.01546  -0.0313   0.1095   0.7464
   5.000   0.6456   0.02669   0.01594  -0.0311   0.1047   0.7497
   5.250   0.6704   0.02728   0.01642  -0.0311   0.1011   0.7532
   5.500   0.6968   0.02783   0.01698  -0.0312   0.0971   0.7566
   5.750   0.7179   0.02838   0.01751  -0.0302   0.0940   0.7591
   6.000   0.7401   0.02900   0.01811  -0.0293   0.0912   0.7620
   6.250   0.7637   0.02961   0.01876  -0.0288   0.0883   0.7654
   6.500   0.7880   0.03026   0.01937  -0.0285   0.0860   0.7689
   6.750   0.8141   0.03102   0.02006  -0.0286   0.0843   0.7724
   7.000   0.8424   0.03185   0.02095  -0.0291   0.0823   0.7760
   7.250   0.8668   0.03263   0.02178  -0.0286   0.0806   0.7787
   7.500   0.8903   0.03341   0.02259  -0.0281   0.0792   0.7815
   7.750   0.9142   0.03421   0.02336  -0.0277   0.0780   0.7847
   8.000   0.9391   0.03516   0.02434  -0.0276   0.0768   0.7886
   8.250   0.9638   0.03622   0.02556  -0.0274   0.0753   0.7928
   8.500   0.9877   0.03727   0.02671  -0.0273   0.0739   0.7968
   8.750   1.0079   0.03821   0.02773  -0.0264   0.0728   0.8000
   9.000   1.0287   0.03917   0.02875  -0.0257   0.0719   0.8035
   9.250   1.0506   0.04023   0.02983  -0.0253   0.0711   0.8073
   9.500   1.0728   0.04150   0.03115  -0.0251   0.0705   0.8113
   9.750   1.0908   0.04317   0.03309  -0.0244   0.0698   0.8152
  10.000   1.1037   0.04479   0.03497  -0.0228   0.0691   0.8186
  10.250   1.1144   0.04648   0.03690  -0.0211   0.0686   0.8226
  10.500   1.1231   0.04828   0.03892  -0.0193   0.0681   0.8272
  10.750   1.1310   0.05028   0.04116  -0.0178   0.0676   0.8320
  11.000   1.1346   0.05227   0.04337  -0.0158   0.0672   0.8361
  11.250   1.1363   0.05437   0.04569  -0.0138   0.0668   0.8405
  11.500   1.1368   0.05660   0.04813  -0.0122   0.0664   0.8451
  11.750   1.1363   0.05900   0.05071  -0.0108   0.0660   0.8497
  12.000   1.1329   0.06136   0.05325  -0.0091   0.0656   0.8539
  12.250   1.1272   0.06404   0.05612  -0.0077   0.0654   0.8586
  12.500   1.1204   0.06700   0.05926  -0.0068   0.0651   0.8638
  12.750   1.1103   0.07032   0.06278  -0.0062   0.0648   0.8685
  13.000   1.0951   0.07423   0.06689  -0.0058   0.0646   0.8733
  13.250   1.0709   0.07950   0.07243  -0.0065   0.0645   0.8779
<< Back to NLR-7301 AIRFOIL (nlr7301-il)

Polar data table (+)

Polar graphs


<< Back to NLR-7301 AIRFOIL (nlr7301-il)