As the early 1994 supersonic carrier configuration the new design embodies a double delta shaped wing and a large, partially open cargo bay on the fuselage bottom to mount the second stages. The ten augmented turbo-engines are located in four nacelles in a 2+3 arrangement beneath the wings. JP(kerosene) propellant is used to carry the fuel inside the wings and therefore to reduce structural loads. In connection with the propulsion system design the DSL aircraft has been modified in late 1996 and early 1997. The fuselage geometry is widely unchanged. But preliminary structural lay-out shows that the second stages could be more closely integrated than in the earlier design without compromising strength. Thus the overall wave drag and base drag is considerably reduced. The wing is redesigned to a NACA 66-airfoil with a moderately negative dihedral angle to improve aerodynamics and supersonic flight stability. Strakes enhance the aircraft's high lift performance. For better maneuverability canards are added at the nose.
Gallery
Last modification of this page: 22. September 1997
Contribution(s) to this page: Martin Sippel