A NUMERICAL INVESTIGATION OF THE 14-XB FOREBODY LEADING-EDGE BLUNTNESS EFFECTS ON THE EXTERNAL AIRFLOW OF THE SCRAMJET INTAKE
João Vitor Marques Brito de Siqueira1; Maurício Antoniazzi Pinheiro Rosa1
1 Instituto de Estudos Avançados - IEAv
doi:10.20906/CPS/COB-2015-0098
Resumo
The Institute for Advanced Studies (IEAv), at the Aerothermodynamics and Hypersonics Division (EAH), has been doing a series of studies with the purpose of developing a hypersonic prototype vehicle powered by a scramjet engine. In this way, numerical simulations have been performed to analyze the hypersonic flow over the inlet of the present vehicle configuration (14-XB) of the 14-X hypersonic vehicle prototype. The objective of this paper was analyzing the influence of the leading edge bluntness, as well as the use of different viscous models, on the formation of the boundary-layer and its interactions with the shock waves from the compression ramp and flow separation that usually occurs there. At first, it has been done an analysis of the influence of the leading-edge bluntness and the use of different viscous models on a hypersonic flow passing over a 9° single wedge and the interaction between the entropy layer and the boundary layer. Secondly, it has been done a validation analysis of the numerical viscous models used for calculating hypersonic flow over a double wedge with blunt leading edge through comparison with experimental data from the literature which has shown that the transitional flow models analyzed yield good results. At last, a numerical study was done for the inlet compression ramps of the 14-XB vehicle. For all analysis, it has been considered different leading edge sizes, wall thermal conditions and viscous flow modeling. Similarly to the sharp leading edge case, the separation bubble increase with wall temperature. Regarding the blunt leading edge size effect on the bubble size, it reaches a maximum at a certain edge radius and then decreases as the radius is further increased.
Palavras-chave: leading-edge bluntness; scramjet inlet; flow separation; hypersonic flow; numerical simulation