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