Numerical simulation of the flow in small bleed orifice at the external flow high speed

The paper presents the results of numerical simulation of the flow around a hypersonic inlet forebody to the entrance to the channel as well as the flow in a single boundary layer bleed channel. Simulation of the flow around the hypersonic inlet forebody has been carried out at Mach numbers M = 3, 4...

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Bibliographic Details
Main Authors: Goldfeld, M. A., Korotaeva, T. A., Turchinovich, A. O.
Format: Conference Proceeding
Language:English
Subjects:
Angle of attack
Bleeding
Boundary layers
Computational fluid dynamics
Computer simulation
Entrances
Hypersonic inlets
Initial conditions
Mathematical models
Orifices
Reynolds averaged Navier-Stokes method
Shock waves
Simulation
Static pressure
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Summary:The paper presents the results of numerical simulation of the flow around a hypersonic inlet forebody to the entrance to the channel as well as the flow in a single boundary layer bleed channel. Simulation of the flow around the hypersonic inlet forebody has been carried out at Mach numbers M = 3, 4 6 and angles of attack of 4° and 6° using numerical solution of the Reynolds- averaged Navier-Stokes equations. Distributions of static pressure along the plane of symmetry and in the transverse direction are presented in the paper. Comparison of the numerical simulation results with experimental data has shown their satisfactory agreement. The parameters behind the bow shock wave obtained at the simulation of the flow around the inlet forebody have been used to specify the initial conditions for simulation of the flow through a boundary layer bleed hole.
ISSN:0094-243X
1551-7616
DOI:10.1063/1.5065212