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    International Journal of Innovative Science and Research Technology
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    The vehicle moving at hypersonic speed experience forces which leads to slow-down of the vehicle.

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    Spherical Blunted Tangential Ogive Nose-Cone for Hypersonic Vehicle

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    The vehicle moving at hypersonic speed experience forces which leads to slow-down of the vehicle.

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    © All Rights Reserved
    Download as PDF, TXT or read online from Scribd
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    57 views4 pages

    Spherical Blunted Tangential Ogive Nose-Cone For Hypersonic Vehicle

    Uploaded by

    International Journal of Innovative Science and Research Technology
    The vehicle moving at hypersonic speed experience forces which leads to slow-down of the vehicle.

    Copyright:

    © All Rights Reserved
    Download as PDF, TXT or read online from Scribd
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    of 4

    Volume 6, Issue 7, July – 2021 International Journal of Innovative Science and Research Technology

    ISSN No:-2456-2165

    Spherical Blunted Tangential Ogive Nose-Cone for


    Hypersonic Vehicle
    Shridhar Savat Suraj Sambhajirao Patil
    Dept. Of Aerospace Engineering Dept. Of Aerospace Engineering
    Lovely Professional University Lovely Professional University

    Abstract:- The vehicle moving at hypersonic speed degenerates the material faster in this process causing
    experience forces which leads to slow-down of the distortion of the hypersonic vehicle shape and increasing
    vehicle. This flow of fluid which makes it slow is known drag coefficient. Such a unique environment in the
    as drag which plays important role while designing hypersonic flow makes the survivability of such vehicles a
    hypersonic rockets for mars mission. Air drag is also unique challenge.
    plays an important role in the designing of the vehicle.
    The objective of the aerospace industry is to develop the The purpose of this paper is designing of the nose cone
    nose cone that can travel at high speed by producing producing least drag on the rocket for mars mission. In this
    optimum value of air drag & force. This investigation paper I am going to discuss the performance of the spherical
    deals with computational analysis of the spherical blunted tangent ogive nose cone for the hypersonic velocity
    blunted tangent ogive nose cone profile of rocket at condition at different Mach number using computational
    hypersonic velocity. The outcome of nose-cone design on fluid dynamics. Flow phenomena observed in numerical
    the drag is studied at hypersonic flow. The paper aim is simulations during Mach 5, 5.02, 5.04 for spherical blunted
    recognize specific aerodynamic characteristics with tangent ogive nose cone. Spherical blunted tangent ogive
    minimum drag at particular Mach number with nose cone profile gives higher critical Mach number and
    considering density, temperature, viscosity, pressure, least drag coefficient which is desirable for the hypersonic
    velocities for the hypersonic flight. The area of this paper flow.
    is to develop some profile with outstanding aerodynamic
    qualities and low cost for use in construction projects for II. PHYSICAL MODEL
    hypersonic mission by improving their efficiency and
    effect on target. The present problem is analysed in Spherical Blunted Tangent Ogive:
    ANSYS fluent software. Flow over a body is observed in The shape profile is formed by a circle segment like
    numerical simulation for particular Mach number for the vehicle body which tangent to the curves of nose cone at
    spherical blunted tangent ogive nose cone profile & the the base. The vogue of this shape is largely due to the
    parameters such as critical design aspects and simplicity of building its profile as shown in figure.
    performance characteristics of the selected nose cone are
    presented.

    Keywords:- Mach Number, Hypersonic Flows, Nose


    Profiles, Aerodynamic, ANSYS Fluid Fluent.

    I. INTRODUCTION

    From many years aerospace projects involve


    designing, manufacturing and launching rockets and
    missiles with payload that perform to reach apogee up to
    mars, moon. But in hypersonic condition nose cone play an
    important role reducing drag force on entire body and not
    allowing flow separation which are adversative effects on
    efficiency of rocket. And I strongly believe that efficiency of
    rocket can be increased by producing minimum drag on
    rocket. The development of hypersonic vehicles is mainly
    limited due to characteristics of the hypersonic flow. When
    vehicle exceeds speed of Mach 5, the stream flow causes
    many uncertainties for the vehicle. One of the major Fig 1.1 Spherical blunted tangential ogive nose cone profile
    difficulties is the creation of high temperature flow bringing
    non equilibrium chemical flow properties such as The profile of nose cone with spherically blunted
    dissociation and ionization. This process chemically reacts tangent ogive shape is created by placing a spherical section
    with material at the surface level of the hypersonic vehicle on the front part of nose cone having tangent ogive shape.

    IJISRT21JUL954 www.ijisrt.com 1594


    Volume 6, Issue 7, July – 2021 International Journal of Innovative Science and Research Technology
    ISSN No:-2456-2165
    The point at which the tangent ogive intersects with the i) Pre-processing - Design, Create Mesh, Set the Boundary
    sphere is called the Tangency point. The tangency point is condition as per requirement and apply Numerical
    determined using: method,
    ii) Processing – In this all the governing equation are solved
    by using numerical method. In this we have use density
    based solver.
    iii) Results – In this we can get results in all the forms such
    as graphs, contour, animation which helps us to
    understand the results easily.

    These steps are used for Ansys Workbench were the


    boundary condition are kept as:-
     Mach No.- 5
     Pressure – 1 ATM
     Temperature – 300K
     Solver Set to 2nd Order Discretisation
     Monitors are set to 10-6.

    III. RESULT AND DISCUSSION

    The results we got from Ansys Fluents for our


    simulation after post-processing are discuss below. As the
    incoming flow was set at hypersonic speed, the bow and
    attached shocks were visible in contour.

     Pressure
    This nose cone shape is designed to travel through
    compressible fluid medium. In case of spherically blunt
    profile, we observe highest mean pressure value on surface
    of body. Thus, to attain minimum tip temperature, parabolic
    nose shape is preferred. To attain the lowest value of mean
    temperature on the surface, we prefer the tangent ogive nose
    design. Also, by using tangent ogive shape for the nose
    cone, we obtain minimum value of mean shear stress at the
    surface.

    Fig 1.3 Pressure Contour spherical blunted tangential ogive


    nosecone

    Fig. 1.2 CAD model of spherical blunted tangential ogive


    nose cone

    Design and Computational Methodology:


    In this paper spherical blunted tangential ogive
    nosecone shape is planned utilizing Solid works software.
    The initial step is to create 2D model. Simulation is done in
    three steps i.e.
    Fig.1.4 Simulation Result Graph of pressure for spherical
    blunted tangential ogive nosecone

    IJISRT21JUL954 www.ijisrt.com 1595


    Volume 6, Issue 7, July – 2021 International Journal of Innovative Science and Research Technology
    ISSN No:-2456-2165
    For spherical blunted tangential nosecone for The static pressure rises in the downstream of the shocks as
    hypersonic flows, there is presence of large amount of a result increases the pressure and temperature. The sudden
    pressure present at the tip of noce cone and the layer near interaction between the nose cone body & the air flow cause
    the blunted surface surrounded by high total pressure layer, disturbance. And this disturbance cause the density variation
    this was due to the variation of shock wave, indicating 3D in the medium which also changes the temperature. It also
    flow characteristics. This can also seen it the above graph. cause equilibrium flow disturbance which will be higher
    Spherical blunted nosecone, there is existence of least than ideal gas. As we can see in the above graph that the
    pressure instantly downstream of the nosecone. In this we sudden rise in the density is cause due the nose cone & also
    can see that the shock wave form at the nose cone it little we can see the formation of shock wave.
    away from nosecone surface and this type is called detached
    shock wave.  Velocity

     Density

    Fig 1.7 Velocity Contour spherical blunted tangential ogive


    Fig 1.5 Density Contour spherical blunted tangential ogive nosecone
    nosecone

    Fig.1.8 simulation results of velocity for spherical blunted


    tangential ogive nosecone

    Fig.1.6 Simulation Result Graph of Density for spherical The sudden change of flow will generate drag and
    blunted tangential ogive nosecone shock wave at the surface of nose cone which can be seen in
    the fig.1.7. The formation of shock wave changes the
    Travelling at higher speed region, nose cone properties of the flow which stops the vehicle to travel fast
    experiences sudden change in the properties of fluid. in the atmosphere & can also damage the vehicle. Now
    Temperature, pressure and density across the shockwave’s when we talk about traveling to other planets we need the
    front changes in downstream condition of the shockwave. rockets which can travel at high speed such as hypersonic

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    Volume 6, Issue 7, July – 2021 International Journal of Innovative Science and Research Technology
    ISSN No:-2456-2165
    which will also cause major changes in the shape of rocket Temperature plays an important role while design the
    in different atmosphere. And this will increase the shock rocket nose cone. It depends on the aerodynamics nature of
    wave force on the rocket and to reduce it we will need more the body. In the above fig. 1.9 we can we that there is
    aerodynamic efficient nose cone. For body to sustain the sudden rise in the temperature at the tip of the nose cone
    hperpersnoic velocities we need to keep the shock wave which can damage the nose cone & also can change the
    away from the main body & which can be only done in shape of the nose cone. This rise in temperature helps in the
    Bluff body due to its large surface area. Bluff body design in selection of the material of the rocket. Sometimes due to rise
    aerodynamics and structural aspects become more crucial in temperature there is layer present of Space Banket at the
    factor in hypervelocity vehicle. As flight velocity reaches to surface of the nose cone. Nose Cone is defined as the Front-
    very high velocity, shockwaves start forming on the most part in an aircraft, Missile or Rocket. Its purpose is to
    spacecraft, which further increases the velocity and pushes withstand extremely high temperature due to Atmospheric
    the shock front closer to the body. Hence, the body design Drag.
    plays very important role as it directly influence the
    shockwave contour. The De-attached shocks which are IV. CONCLUSION
    generated on body basically nose cone part of aircraft or
    spacecraft travelling at higher velocity region has some The reason for this paper is to help the researcher
    phenomenal use in aerospace industry. As the bow shock while selecting the nose cone for the hypersonic vehicle and
    generate away from the surface, higher velocity was also for performance improvement of hypersonic flight
    achievable. Blunt body design nose cone, re- entry vehicle nosecone using spherical blunted tangential ogive nosecone.
    experience bow shock during the operations. By referring above outcomes of spherical blunted tangential
    ogive nosecone for higher critical Mach number which is
     Temperature desirable for hypersonic flows as stated in problem
    statement. This paper demonstrations the flows
    characteristics, such as aerodynamic drag, pressure, velocity,
    Temperature and attached shock wave formed ahead of the
    spherical blunted tangent ogive cone at zero angle of attack
    near the nose cones.

    REFERENCES

    [1]. “A. Hemateja, B. Ravi Teja , A. Dileep Kumar ,


    Rakesh S.G”, “IOP Conference Series: Materials
    Science and Engineering”, “2017”.
    [2]. “Niranjan Sahoo”, “16th Australasian Fluid Mechanics
    Conference”, “2007”.
    [3]. “Ashish Narayan, S Narayanan and Rakesh Kumar”,
    “Simulation: Transactions of the Society for Modeling
    and Simulation International”, “2017”.
    [4]. “Manjunatha H, C. N. Nataraj”, “International Journal
    Fig 1.9 Temperature Contour spherical blunted tangential of Science and Research (IJSR)”, “2014”.
    ogive nosecone [5]. “N. S. Harshavardhan .R; Sanjana .K; Sai Sharan .K ;
    Srinivas .G”, “International Journal of Scientific &
    Engineering Research, Volume 5, Issue 5”, “May-
    2014”.
    [6]. “Guillaume Grossir, Fabio Pinna, Olivier Chazot”,
    “AIAA Journal”, “1999”.
    [7]. “W. Schuyler Hinman, Craig T. Johansen”,
    “Aerospace Science and Technology”, “2016”.

    Fig.1.10 Simulation Result Graph of temperature for


    spherical blunted tangential ogive nosecone

    IJISRT21JUL954 www.ijisrt.com 1597

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