Mixed compression inlets of the type used for supersonic air breathing engines, such as for the SR-71 and the supersonic transport aircraft, perform efficiently at speeds of around Mach 2.0 to 2.5. These inlets are highly susceptible to unstart when operating in a fuel efficient configuration. An unstart margin allows perturbations in mass flow and incoming flow incidence angle, which result from combinations of many contributors, which may include: gust, engine misalignment, control system tolerance, sidewash and upwash due to maneuver, and structural flexibility effects. This paper develops a methodology by which the last two effects may be analyzed to determine their contribution to changes in incoming flow incidence angle.
Impacts of Structural Dynamics on Engine Inlet Flow Characteristics
Sae Technical Papers
World Aviation Congress & Exposition ; 1998
1998-09-28
Aufsatz (Konferenz)
Englisch
Impacts of Structural Dynamics on Inlet Flow Incidence Angle and Inlet Unstart
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