A 2D Mach 2.2 internal compression inlet with 97 % total pressure recovery has been designed using viscid-inviscid computational tools. Losses are minimized by careful boundary layer management combined with shape design for weak shocks. The resulting inlet has reduced stability to unstart in the face of atmospheric and engine-born disturbances, necessitating the use of an active stabilization bleed system that recovers the disturbance-rejection capabilities required of modem inlets. Atmospheric disturbances that the inlet may encounter during supersonic flight are characterized. Two separate physical mechanisms for unstart are identified, and active control algorithms to prevent these forms of unstart are designed and demonstrated using 1D and 2D unsteady Euler simulations. The resulting actively stabilized inlet can withstand flight velocity, temperature, and angle of attack perturbations consistent with atmospheric flight.
Design of an actively stabilized near-isentropic supersonic inlet
Entwurf eines aktiv stabilisierten nahezu isentropen Überschalleinlaufs
AIAA Computational Fluid Dynamics Conference, 16 ; 1551-1561
2003
11 Seiten, 14 Bilder, 1 Tabelle, 14 Quellen
Aufsatz (Konferenz)
Englisch
Design of a Near-Isentropic Supersonic Inlet Using Active Control
Online Contents | 2005
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