Performance assessment of supersonic and hypersonic intake systems with nano-particle injection

A novel approach to improve the performance of supersonic and hypersonic intake systems with nano-particle injection has been studied. A parametric study using Mach number (M∞), Stokes number (Stk), particle Eckert number (Ecp), and thermal transport number (αt) was conducted across a quasi-1D converging-diverging (C-D) supersonic intake at idealized and single-shock compression cases. Gains in stagnation pressure recovery were achieved for both the cases. Gains were observed in the idealized compression case when: Ecp>0.25 and αt>0.5 for a Mach number of 2.5; and Ecp>0.5 and αt>0.7 for a Mach number of 5. The results also showed that a combination of cooling, momentum exchange, and particle size is required to enhance intake performance. A rectangular mixed-compression intake at Mach 3 was simulated using an unsteady compressible gas-particle CFD solver in OpenFOAM. CFD simulations with nano-particle injection predicted a 16% gain in the exit pressure recovery. •Effect of nano-particle injection on supersonic intakes is studied.•A 1D study was conducted for isentropic and single-shock compression cases.•The CFD study was conducted across a 2D mixed compression intake at Mach 3.•Considerable gains in pressure recovery were achieved with nano-particles.