A high-speed civil transport inlet at Mach 2 and angle of attack is simulated by using a three-dimensional Navier-Stokes solver with the Baldwin-Lomax algebraic turbulence model. An extrapolation uniform mass bleed boundary condition for the slot bleed is successfully employed. At zero angle of attack and critical operation, the computational pressure distribution agrees well with the experiment. The location and intensity of the terminal shock and the total pressure recovery are accurately computed. The predicted steady-state distortion deviates from the experiment. The computed maximum angle of attack that the inlet can sustain before unstart is in good agreement with the experiment. Mesh refinement results are presented.
ASJC Scopus subject areas
- Aerospace Engineering