Authors :
Shridhar Savat; Suraj Sambhajirao Patil
Volume/Issue :
Volume 6 - 2021, Issue 7 - July
Google Scholar :
http://bitly.ws/9nMw
Scribd :
https://bit.ly/38m7W8c
Abstract :
The vehicle moving at hypersonic speed
experience forces which leads to slow-down of the
vehicle. This flow of fluid which makes it slow is known
as drag which plays important role while designing
hypersonic rockets for mars mission. Air drag is also
plays an important role in the designing of the vehicle.
The objective of the aerospace industry is to develop the
nose cone that can travel at high speed by producing
optimum value of air drag & force. This investigation
deals with computational analysis of the spherical
blunted tangent ogive nose cone profile of rocket at
hypersonic velocity. The outcome of nose-cone design on
the drag is studied at hypersonic flow. The paper aim is
recognize specific aerodynamic characteristics with
minimum drag at particular Mach number with
considering density, temperature, viscosity, pressure,
velocities for the hypersonic flight. The area of this paper
is to develop some profile with outstanding aerodynamic
qualities and low cost for use in construction projects for
hypersonic mission by improving their efficiency and
effect on target. The present problem is analysed in
ANSYS fluent software. Flow over a body is observed in
numerical simulation for particular Mach number for
spherical blunted tangent ogive nose cone profile & the
parameters such as critical design aspects and
performance characteristics of the selected nose cone are
presented.
Keywords :
Mach Number, Hypersonic Flows, Nose Profiles, Aerodynamic, ANSYS Fluid Fluent.
The vehicle moving at hypersonic speed
experience forces which leads to slow-down of the
vehicle. This flow of fluid which makes it slow is known
as drag which plays important role while designing
hypersonic rockets for mars mission. Air drag is also
plays an important role in the designing of the vehicle.
The objective of the aerospace industry is to develop the
nose cone that can travel at high speed by producing
optimum value of air drag & force. This investigation
deals with computational analysis of the spherical
blunted tangent ogive nose cone profile of rocket at
hypersonic velocity. The outcome of nose-cone design on
the drag is studied at hypersonic flow. The paper aim is
recognize specific aerodynamic characteristics with
minimum drag at particular Mach number with
considering density, temperature, viscosity, pressure,
velocities for the hypersonic flight. The area of this paper
is to develop some profile with outstanding aerodynamic
qualities and low cost for use in construction projects for
hypersonic mission by improving their efficiency and
effect on target. The present problem is analysed in
ANSYS fluent software. Flow over a body is observed in
numerical simulation for particular Mach number for
spherical blunted tangent ogive nose cone profile & the
parameters such as critical design aspects and
performance characteristics of the selected nose cone are
presented.
Keywords :
Mach Number, Hypersonic Flows, Nose Profiles, Aerodynamic, ANSYS Fluid Fluent.
