Scheme and Inlet Performance of Supersonic Business M=1.6 Cruise Aircraft

Abstract

High efficient inlet prototype including supersonic inlet and subsonic large curvature diffuser was developed and chosen for supersonic business aircraft with M∞=1.6 cruise flight. Preliminary deceleration of incoming airflow and boundary layer control are provided by means of a swept wedge placed in front of inlet due to forming transverse pressure gradient. Further compression is realized in a system of 3-D shocks with terminal normal one. Numerical modeling based on solution of 3-D Navier-Stokes equations allowed obtaining the results of inlet flow at throttle modes under M∞=0.8-1.8 and confirmed flow stability at 1.5..5-fold increased pressure in subsonic diffuser outlet section in comparison with external free stream pressure. Parametric flow calculations are organized and inlet throttle performance is determined with subsonic diffuser at M∞=0.8-1.8 and boundary layer suction in a throat. It is received that using the boundary layer control with air suction rate Gsuct/Ginlet = 2…5% the total pressure recovery coefficient σ grows up to σ = 0.89…0.97 for considered M∞ range. Nomenclature p = pressure, p =p/p ∞ = normalized static pressure, p thrott=pthrott/p ∞ = throttling ratio,