The unsteady aerodynamics of the delta wing, high cross range, shuttle orbiter have been investigated. Three potentially dangerous flow separation phenomena involving the delta wing have been identified, each of which could seriously compromise the flight dynamics. They are (1) leeside shock-induced separation, (2) sudden leading-edge stall, and (3) the subsonic leading-edge vortex and vortex burst. Each of these unsteady flow phenomena can be triggered by control surface deflection. Furthermore, wing stall and control-induced separation effects interact with the relatively large fuselage, causing simultaneous alteration of the lateral-directional stability. Trajectory shaping may be the most powerful means of dealing with these stall effects.
Delta wing separation can dominate shuttle dynamics.
American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference
1972-09-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Delta wing separation can dominate shuttle dynamics
AIAA | 1972
|Effects of Delta Wing Separation on Shuttle Dynamics
AIAA | 1973
|Review of delta Wing Space Shuttle Vehicle Dynamics
NTIS | 1971
|Review of delta wing space shuttle vehicle dynamics
NTRS | 1972
|Review of delta wing space shuttle vehicle dynamics
NTRS | 1971
|