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AERODYNAMIC HEAT FLUX ESTIMATION FOR A LAUNCH VEHICLE

Rony C. Varghese
Aerothermal Design and Analysis Division Vikram Sarabhai Space Centre

Sundar B
Aerodynamic Characterization Division Vikram Sarabhai Space Centre Thiruvavanthapuram

M. J. Chacko
Aerothermal Design and Analysis Division Vikram Sarabhai Space Centre Thiruvananthapuram

DOI: 10.1615/IHMTC-2017.1450
pages 1041-1045

摘要

During atmospheric flight of a launch vehicle, it encounters severe thermal environment. The kinetic energy of air is converted into thermal energy which results in aerodynamic heating.
Aerodynamic heating analysis involves evaluation of heat flux on the body along a trajectory due to air flow and the thermal response of the structure to this heat flux. For design purpose, trajectory wise analysis is required. Hence engineering method results in the quick estimation of aerodynamic thermal environment compared to CFD.
A design code has been used as an integrated package by patching together applicable theories for various regions like stagnation regions and aft body and for different flow conditions like laminar and turbulent flows in continuum and free molecular flow regime for heat flux estimation and thermal response for studying the requirement of thermal protection system.
To start the computation, the free-stream properties away from the body need to be evaluated first. From the trajectory data, the altitude and velocity of the re-entry body at any instant of time are known. From a reference atmosphere model, the free stream properties like temperature, pressure and density are evaluated based on altitude. Pressure distribution along the body is used for the computation. After obtaining the pressure distribution, density and temperature at the boundary layer edge are obtained from the post shock conditions, in an iterative manner using isentropic relations and the equilibrium air properties.
In this paper, the methodology of heat flux estimation using various engineering methods for estimating the heat transfer rates over the body of a launch vehicle and thermal response of the structure is described. The methodology of heat flux estimation and thermal response analysis is validated using direct flight measurements.

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