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DAE 11
# Daedalus wing center panel airfoil. Design Re = 500K
1.000000 0.000000
0.986485 0.002537
0.970011 0.005613
0.947881 0.010041
0.918618 0.016374
0.887980 0.023556
0.857968 0.031118
0.827970 0.039139
0.797803 0.047590
0.767378 0.056399
0.736634 0.065482
0.705687 0.074715
0.675260 0.083695
0.645478 0.092177
0.616310 0.099961
0.587628 0.106875
0.559192 0.112804
0.530735 0.117738
0.502104 0.121740
0.473284 0.124848
0.444338 0.127068
0.415323 0.128391
0.386255 0.128806
0.357167 0.128336
0.328135 0.126996
0.299232 0.124754
0.270512 0.121609
0.242030 0.117536
0.213885 0.112508
0.186216 0.106500
0.159197 0.099489
0.133039 0.091476
0.108024 0.082466
0.084520 0.072514
0.062995 0.061754
0.044085 0.050490
0.028485 0.039251
0.016619 0.028679
0.008417 0.019287
0.003417 0.011421
0.000883 0.005097
0.000128 0.000182
0.000626 -0.003555
0.002138 -0.006473
0.004541 -0.008835
0.008212 -0.010744
0.014240 -0.012418
0.024697 -0.013921
0.041573 -0.014931
0.065014 -0.015107
0.092723 -0.014502
0.122696 -0.013331
0.153786 -0.011784
0.185487 -0.010003
0.217549 -0.008087
0.249834 -0.006102
0.282263 -0.004093
0.314698 -0.002099
0.347047 -0.000149
0.379318 0.001724
0.411508 0.003509
0.443624 0.005174
0.475671 0.006709
0.507637 0.008092
0.539527 0.009282
0.571366 0.010264
0.603162 0.011026
0.634928 0.011552
0.666677 0.011849
0.698414 0.011916
0.730135 0.011759
0.761819 0.011381
0.793447 0.010763
0.825020 0.009891
0.856580 0.008751
0.888343 0.007325
0.920025 0.005610
0.948000 0.003865
0.969655 0.002348
0.986285 0.001076
1.000000 0.000000
|
