Hypersonic Inlet Flow Analysis at Ofi-Design Conditions

The ∞ow characteristics of a flxed-geometry hypersonic inlet for high-speed propulsion are examined using both computational and theoretical aerodynamics. Numerical simulations are presented for an inlet-cowl conflguration designed for shock-on-lip condition at Mach 5.5. The fundamental interactions between shock and expansion waves at inlet are investigated at ofi-design Mach numbers from 4 to 6. E‐ciency parameters are evaluated for several conflgurations. Various ofi-design wave interactions are considered for the inlet. These can result in either shock attachment or detachment at the cowl lip depending on the position of the cowl and centrebody with the incoming shock system. The re∞ected wave system from the cowl can undergo either regular re∞ection or Mach re∞ection on the centrebody. Interaction of wave systems at inlet can result in high aerodynamic losses and ∞ow non-uniformities which afiect inlet performance. In addition, inlet wave interactions can lead to shock impingement on the forebody, centrebody and cowl boundary layer and can result in ∞ow separations. This paper presents a set of design and ofi-design computations for a real intake conflguration. It also presents a parameter study to focus on the essential details of the shock-shock and shock-expansion interactions to predict ∞ow phenomena at inlet.