The unsteady aerodynamics of the delta planform, high cross range, shuttle orbiter were investigated. It has been found that these vehicles are subject to five unsteady flow phenomena that could compromise the flight dynamics. They are: (1) leeside shock induced separation, (2) sudden leading edge stall, (3) vortex burst, (4) bow shock-flap shock interaction, (5) forebody vorticity. Trajectory shaping is seen as the most powerful means of avoiding the detrimental effects of the stall phenomena. However, stall must be fixed or controlled when traversing the stall region. The other phenomena may be controlled by carefully programmed control deflections and some configuration modification. Ways to alter the occurrence of the various flow conditions are explored.
Review of delta wing space shuttle vehicle dynamics
1972-02-01
Conference paper
No indication
English
Review of delta Wing Space Shuttle Vehicle Dynamics
NTIS | 1971
|Review of delta wing space shuttle vehicle dynamics
NTRS | 1971
|Delta wing separation can dominate shuttle dynamics
AIAA | 1972
|Delta wing separation can dominate shuttle dynamics.
NTRS | 1972
|Effects of Delta Wing Separation on Shuttle Dynamics
AIAA | 1973
|