LAUSR

Abstract 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 ( S t k ), particle Eckert number ( E c p ), and thermal transport number ( α t ) 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: E c p > 0.25 and α t > 0.5 for a Mach number of 2.5; and E c p > 0.5 and α t > 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.