INVESTIGATION OF FLOW FIELD AROUND REUSABLE LAUNCH VEHICLE WITH DIFFERENT FUSELAGE CROSS SECTION AT SUPERSONIC SPEED

Document Type : Primary Research paper

Authors

Department of Aeronautical Engineering, Nehru Institute of Technology, Coimbatore

Abstract

In present study, an computational works has been
carried out on different cross sections circular, hemispherical,
triangular and rectangular models by taking the boundary
conditions of Saturn V launch Vehicle at mach numbers 1.5, 2.7
and 4.4 considering flat angles to obtain the complex flow
features and forces acting on the RLV models at supersonic
speed. From the computation the losses in reusable launch
vehicles at various sections has been determined by considering
Three factors Strength of the shock, Aerodynamic heating and
retardation of velocity in the base region by taking rate of
change of entropy, temperature and velocity respectively. losses
from these three factors are compared and a brief investigation is
done on the models from which it was concluded that based on
shock strength and aerodynamic heating circular cross-section
had good aerodynamic characteristics and it was found that
triangular model has a good aerodynamic characteristics as for
as body of launch vehicle is concerned

Keywords

Int. J. of Aquatic Science
Volume 12, Issue 3 - Serial Number 3
ICMMNT-2021 International Virtual Conference on Materials, Manufacturing and Nanotechnology, 30th June, 2021.
June 2021
Pages 485-490

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