Airfoil: E387 (E)
Builder: Y. Tinel
Comment: 'u.s.t. located at 2% chord, l.s.t. located at 5% chord' 

Number of Reynolds #'s:
5

Average Reynolds #:
99963
Number of angles of attack:
61
 alpha  /   Cl   /  Cm
-10.17   -0.471   0.0533
 -9.16   -0.434   0.0408
 -8.15   -0.398   0.0269
 -7.14   -0.386   0.0079
 -6.18   -0.332  -0.0183
 -5.19   -0.258  -0.0556
 -4.21   -0.108  -0.0587
 -3.18    0.039  -0.0865
 -2.11    0.185  -0.0891
 -1.11    0.280  -0.0869
 -0.06    0.385  -0.1013
  0.89    0.472  -0.0923
  1.96    0.573  -0.0840
  3.00    0.675  -0.0893
  4.02    0.769  -0.0742
  5.04    0.872  -0.0670
  6.08    0.979  -0.0761
  7.09    1.072  -0.0729
  8.14    1.138  -0.0665
  9.15    1.191  -0.0571
 10.17    1.230  -0.0427
 11.13    1.250  -0.0544
 12.16    1.254  -0.0518
 13.16    1.251  -0.0537
 14.08    1.205  -0.1200
 15.08    1.119  -0.1515
 16.01    1.082  -0.1581
 17.00    1.083  -0.1639
 18.02    1.063  -0.1665
 19.05    1.077  -0.1694
 20.01    1.087  -0.1773
 19.50    1.074  -0.1822
 18.52    1.054  -0.1723
 17.54    1.073  -0.1763
 16.50    1.074  -0.1704
 15.51    1.076  -0.1625
 14.53    1.100  -0.1467
 13.64    1.246  -0.0565
 12.67    1.257  -0.0442
 11.67    1.256  -0.0442
 10.67    1.247  -0.0492
  9.64    1.219  -0.0538
  8.65    1.165  -0.0664
  7.69    1.115  -0.0643
  6.56    1.026  -0.0693
  5.59    0.928  -0.0732
  4.51    0.825  -0.0768
  3.46    0.719  -0.0921
  2.50    0.629  -0.1016
  1.45    0.528  -0.0966
  0.38    0.431  -0.1064
 -0.60    0.338  -0.0973
 -1.65    0.239  -0.0999
 -2.71    0.114  -0.0958
 -3.67   -0.036  -0.0804
 -4.73   -0.187  -0.0706
 -5.69   -0.322  -0.0391
 -6.72   -0.372  -0.0181
 -7.71   -0.415   0.0080
 -8.69   -0.433   0.0246
 -9.65   -0.440   0.0311
Tabulated from data in file bm04988.dat & reduced using program C10.20

Average Reynolds #:
200028
Number of angles of attack:
61
 alpha  /   Cl   /  Cm
-10.17   -0.477   0.0468
 -9.12   -0.485   0.0408
 -8.19   -0.469   0.0306
 -7.14   -0.428   0.0055
 -6.17   -0.368  -0.0210
 -5.19   -0.169  -0.0801
 -4.21   -0.036  -0.0866
 -3.16    0.059  -0.0890
 -2.13    0.154  -0.0875
 -1.11    0.255  -0.0866
 -0.08    0.350  -0.0839
  0.94    0.452  -0.0793
  1.97    0.550  -0.0784
  3.00    0.640  -0.0765
  4.02    0.734  -0.0750
  5.04    0.829  -0.0734
  6.10    0.925  -0.0707
  7.10    1.018  -0.0696
  8.13    1.105  -0.0662
  9.15    1.191  -0.0637
 10.19    1.237  -0.0590
 11.14    1.236  -0.0549
 12.17    1.240  -0.0539
 13.17    1.237  -0.0564
 14.19    1.225  -0.0627
 15.05    1.216  -0.1529
 16.04    1.110  -0.1660
 17.03    1.081  -0.1718
 18.00    1.047  -0.1726
 18.97    1.040  -0.1741
 19.98    1.035  -0.1751
 19.42    1.032  -0.1784
 18.49    1.063  -0.1777
 17.51    1.080  -0.1785
 16.55    1.127  -0.1780
 15.57    1.177  -0.1614
 14.63    1.238  -0.1050
 13.65    1.223  -0.0592
 12.60    1.230  -0.0556
 11.64    1.237  -0.0560
 10.63    1.240  -0.0578
  9.66    1.213  -0.0630
  8.56    1.138  -0.0661
  7.57    1.060  -0.0698
  6.57    0.968  -0.0714
  5.62    0.880  -0.0726
  4.52    0.780  -0.0746
  3.50    0.687  -0.0753
  2.46    0.596  -0.0773
  1.47    0.507  -0.0786
  0.46    0.413  -0.0842
 -0.59    0.311  -0.0844
 -1.63    0.208  -0.0879
 -2.71    0.107  -0.0862
 -3.65    0.018  -0.0878
 -4.76   -0.090  -0.0890
 -5.75   -0.270  -0.0550
 -6.69   -0.401  -0.0097
 -7.68   -0.454   0.0186
 -8.65   -0.470   0.0344
 -9.66   -0.469   0.0422
Tabulated from data in file bm04990.dat & reduced using program C10.20

Average Reynolds #:
350084
Number of angles of attack:
47
 alpha  /   Cl   /  Cm
 -8.18   -0.487   0.0256
 -7.22   -0.435   0.0009
 -6.21   -0.317  -0.0466
 -5.19   -0.161  -0.0805
 -4.14   -0.049  -0.0831
 -3.19    0.048  -0.0825
 -2.15    0.153  -0.0819
 -1.14    0.249  -0.0808
 -0.08    0.351  -0.0797
  0.94    0.451  -0.0790
  1.99    0.556  -0.0785
  3.02    0.664  -0.0778
  4.08    0.769  -0.0768
  5.04    0.862  -0.0755
  6.10    0.963  -0.0740
  7.10    1.047  -0.0711
  8.18    1.142  -0.0687
  9.11    1.205  -0.0650
 10.16    1.260  -0.0604
 11.15    1.274  -0.0587
 12.13    1.279  -0.0625
 13.15    1.269  -0.0667
 14.15    1.262  -0.0748
 15.19    1.249  -0.0834
 14.66    1.254  -0.0786
 13.66    1.275  -0.0710
 12.64    1.275  -0.0648
 11.66    1.287  -0.0611
 10.61    1.275  -0.0580
  9.61    1.236  -0.0629
  8.63    1.179  -0.0671
  7.63    1.092  -0.0699
  6.58    1.003  -0.0727
  5.57    0.909  -0.0750
  4.50    0.809  -0.0768
  3.52    0.710  -0.0783
  2.44    0.605  -0.0791
  1.46    0.502  -0.0798
  0.42    0.397  -0.0804
 -0.61    0.296  -0.0806
 -1.61    0.208  -0.0826
 -2.66    0.099  -0.0835
 -3.70   -0.007  -0.0839
 -4.73   -0.104  -0.0844
 -5.73   -0.236  -0.0689
 -6.69   -0.382  -0.0240
 -7.68   -0.460   0.0131
Tabulated from data in file bm04992.dat & reduced using program C10.20

Average Reynolds #:
349956
Number of angles of attack:
21
 alpha  /   Cl   /  Cm
 10.25    1.270  -0.0204
 11.27    1.285  -0.0207
 12.29    1.281  -0.0206
 13.22    1.280  -0.0206
 14.18    1.278  -0.0205
 15.23    1.259  -0.0202
 16.22    1.197  -0.0193
 17.17    1.151  -0.0185
 18.21    1.061  -0.0171
 19.18    1.049  -0.0169
 20.13    1.054  -0.0169
 19.66    1.056  -0.0170
 18.66    1.058  -0.0170
 17.63    1.120  -0.0180
 16.57    1.192  -0.0192
 15.62    1.258  -0.0202
 14.60    1.270  -0.0204
 13.81    1.280  -0.0206
 12.81    1.281  -0.0206
 11.74    1.278  -0.0205
 10.70    1.281  -0.0206
Tabulated from data in file bm05120.dat & reduced using program C10.20

Average Reynolds #:
499933
Number of angles of attack:
43
 alpha  /   Cl   /  Cm
 -7.81   -0.484   0.0165
 -6.21   -0.313  -0.0495
 -5.19   -0.171  -0.0784
 -4.16   -0.054  -0.0807
 -3.16    0.048  -0.0803
 -2.13    0.150  -0.0799
 -1.12    0.247  -0.0792
 -0.06    0.360  -0.0789
  0.97    0.459  -0.0774
  1.98    0.570  -0.0770
  3.03    0.677  -0.0765
  4.00    0.774  -0.0752
  5.04    0.877  -0.0740
  6.10    0.970  -0.0720
  7.11    1.056  -0.0701
  8.07    1.149  -0.0681
  9.18    1.216  -0.0642
 10.12    1.239  -0.0597
 11.15    1.235  -0.0608
 12.17    1.247  -0.0633
 13.13    1.246  -0.0702
 14.12    1.240  -0.0807
 13.62    1.251  -0.0758
 12.66    1.246  -0.0679
 11.61    1.245  -0.0629
 10.65    1.240  -0.0599
  9.60    1.233  -0.0612
  8.62    1.183  -0.0657
  7.60    1.102  -0.0684
  6.56    1.014  -0.0710
  5.53    0.922  -0.0729
  4.53    0.827  -0.0745
  3.55    0.732  -0.0754
  2.47    0.620  -0.0767
  1.43    0.516  -0.0775
  0.39    0.407  -0.0785
 -0.58    0.305  -0.0793
 -1.64    0.196  -0.0797
 -2.62    0.101  -0.0805
 -3.70   -0.010  -0.0802
 -4.73   -0.107  -0.0816
 -5.69   -0.232  -0.0694
 -6.72   -0.372  -0.0292
Tabulated from data in file bm04994.dat & reduced using program C10.20

File e387_tf.lft created using program C10.20 on Thu May 22 17:01:21 2003
