Three dimensional vortex modes of hypersonic steady-state flow on the blunted bodies leading age

Abstract

In the present work, the non-uniqueness problem of a steady-state hypersonic flow on the leading edge of blunted bodies is investigated experimentally and through direct numeric simulation using FLUENT Navier-Stokes code. The main purpose of numeric investigations is to determine whether 3D vortex structures are one of the steady modes of Navier-Stokes solutions, or whether they appear as a result of insufficient grid resolution and perturbation of lateral boundary conditions. One of the most important experimental results is the reproduction of a single 3D vortex pair in a nominally uniform incoming flow at Mach number M ∞ ∞ ∞ ∞ =8 and a range of Reynolds number Re ∞ ∞ ∞ ∞ =[3160 ÷ ÷ ÷ ÷ 13000]. Nomenclature M = Mach number M r = Mach number of the reverse jet between vortices Re = Reynolds number R = cylinder radius L = spanwise size of the body ϕ = wedge half-angle λ = wave length (period) T = temperature P = pressure P' 0n = total pressure past the normal shock ρ = density q = heat flux [Wt/m 2 ] Q = dimensionless heat flux ∞ = index of free stream parameter 0 = index of stagnation parameter