Hypersonic boundary layer flow at an axisymmetric stagnation point on a blunt body
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Mahesh Kumari
Abstract
A boundary layer analysis is presented for hypersonic flow at an axisymmetric stagnation point region of a blunt body under isothermal and adiabatic boundary conditions. Consideration is given to variable properties of air. It has been shown that surface drag and heat transfer rates may be controlled by applying magnetic field and vectored surface mass transfer. The range of Mach numbers considered is 1–10. As the magnetic field strength M increases, friction factor and heat transfer rate (in the case of isothermal surface) or surface temperature (in the case of adiabatic surface) increase.Friction factor and surface temperature (in the case of adiabatic surface) can be reduced by applying vectored surface mass transfer.
Notation list
- ∞
-
reference free stream conditions
- C 1
-
ratio of density – viscosity producy
- C 2
-
ratio of density – thermal conductivity product
- C fx
-
local skin friction coefficient
- C p
-
specific heat
- du e /dx
-
velocity gradient at the stagnation point
- e
-
conditions at the boundary layer edge
- f
-
nondimensional stream function
- g
-
nondimensional temperature
- h
-
specific enthalpy
- H
-
total enthalpy
- k
-
thermal conductivity
- M
-
Magnetic Parameter (Hartmann number)
- Ma
-
Mach number
- Nu x
-
Nusselt number
- Pr
-
Prandtl number
- q
-
heat flux
- r
-
recovery factor
- r 0
-
radius of curvature of axisymmetric body
- Re x
-
Reynolds number
- St
-
Stanton number
Subscripts
- T
-
temperature
- T ve
-
Vibrational eigen temperature
- u
-
velocity component in streamwise direction
- v
-
velocity component in normal direction
- w
-
conditions at the wall
- x
-
coordinate along streamwise direction
- y
-
coordinate normal to the surface
- β
-
pressure gradient parameter
- γ
-
ratio of specific heats
- η
-
nondimensional coordinate
- μ
-
viscosity
- ρ
-
density
-
-
Eckert number
Acknowledgement
One of the authors (MK) is thankful to the Chairperson, Supercomputer Education and Research Centre, Indian Institute of Science, Bangalore, India, for providing computational facility.
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Research ethics: Not applicable.
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Informed consent: Not applicable.
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Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Use of Large Language Models, AI and Machine Learning Tools: None declared.
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Conflict of interest: The authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
References
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Artikel in diesem Heft
- Frontmatter
- Simulation and analysis of the over-expanded flow field in asymmetric nozzles with lateral expansion
- Design optimization of a fluidic thrust vectoring system based on coanda effect using meta-models
- Research on vibration damping of integral squeeze film damper based on fan rotor tester of turbofan
- Influence of conical shaft stiffness on the dynamic characteristics of flexible rotor
- A novel design methodology for preventing dislocation in the Zig-zag shroud
- Numerical study of effect of the casing slot on the tip leakage vortex and vortex cavitation of a fuel pump
- Multi-parameter study on array-jets impingement with crossflow temperature effect
- Exploration of shock-induced flow dynamics and turbulence-driven combustion optimization in advanced cavity configurations of hydrogen fueled scramjet combustors
- A part-load performance analysis method for gas turbines based on the stage by stages model of the power turbine
- Effect of lip-thickness on rectangular nozzle co-flowing subsonic jet
- Numerical analysis of pollutant formation and exhaust emission in a short annular combustor under part load operation
- Analysis of leakage characteristics and structural optimization of two-stage floating ring seal
- Hypersonic boundary layer flow at an axisymmetric stagnation point on a blunt body
- Numerical simulations of a turbulent lifted hydrogen flame in vitiated coflow with flamelet generated manifold approach
- Optimization of labyrinth seal leakage with independently varied tooth parameters using efficient global optimization
- Investigations of modified cooling hole injection angle configurations for improved trench film cooling performance
- Influence of non-axisymmetric endwall profiling under incoming vortex on the corner separation of a diffusion cascade
- Impact of annular ribs in sudden expansion flow conditions to control base pressure
- Effect of preheated swirling multi-annular jets on mixing and flow characteristics in various expanded confinements
