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Theoretical and numerical investigation of wedge and cone nose profiles at supersonic speed.

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Title: Theoretical and numerical investigation of wedge and cone nose profiles at supersonic speed.
Authors: Kumar, Uttam1 (AUTHOR), Kumar, Rakesh1 (AUTHOR) rakesh@iitism.ac.in
Source: Numerical Heat Transfer: Part A -- Applications. 2025, Vol. 86 Issue 15, p5329-5353. 25p.
Subjects: Mach number, Compressibility (Fluids), Aerodynamic load, Kinetic energy, Projectiles, Shock waves
Abstract: This research endeavor seeks to analyze the nose shapes of a wedge and a cone through simulations conducted with the ANSYS-FLUENT software. When designing missiles and aerodynamic vehicles for high speed, the selection of nose shape is thought to be the most crucial. The aerodynamic bodies traveling at supersonic speeds experience a pronounced influence of fluid compressibility, wherein high-speed fluid particles impart their kinetic energy as heat upon interacting with the frontal surface. The primary difficulty is that missiles and aerodynamic vehicles with high aerodynamic loads depend heavily on the shape of their noses. Therefore, the purpose of this research work is to compare the shape of the wedge and the conical nose at Mach number 2.0. A numerical simulation is used to estimate aerodynamic properties such as downstream Mach number, shock wave angle, pressure ratio, density ratio, temperature ratio, and aerodynamic coefficient, and the results are compared with theoretical results, which are obtained to solve oblique shock relation and Taylor–Maccoll equation. The conical-shaped nose model exhibits superior aerodynamic characteristics compared to the wedged-shaped nose. [ABSTRACT FROM AUTHOR]
Copyright of Numerical Heat Transfer: Part A -- Applications is the property of Taylor & Francis Ltd and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
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DbLabel: Engineering Source
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  Data: Theoretical and numerical investigation of wedge and cone nose profiles at supersonic speed.
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  Data: <searchLink fieldCode="AR" term="%22Kumar%2C+Uttam%22">Kumar, Uttam</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Kumar%2C+Rakesh%22">Kumar, Rakesh</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> rakesh@iitism.ac.in</i>
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  Data: <searchLink fieldCode="JN" term="%22Numerical+Heat+Transfer%3A+Part+A+--+Applications%22">Numerical Heat Transfer: Part A -- Applications</searchLink>. 2025, Vol. 86 Issue 15, p5329-5353. 25p.
– Name: Subject
  Label: Subjects
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Mach+number%22">Mach number</searchLink><br /><searchLink fieldCode="DE" term="%22Compressibility+%28Fluids%29%22">Compressibility (Fluids)</searchLink><br /><searchLink fieldCode="DE" term="%22Aerodynamic+load%22">Aerodynamic load</searchLink><br /><searchLink fieldCode="DE" term="%22Kinetic+energy%22">Kinetic energy</searchLink><br /><searchLink fieldCode="DE" term="%22Projectiles%22">Projectiles</searchLink><br /><searchLink fieldCode="DE" term="%22Shock+waves%22">Shock waves</searchLink>
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: This research endeavor seeks to analyze the nose shapes of a wedge and a cone through simulations conducted with the ANSYS-FLUENT software. When designing missiles and aerodynamic vehicles for high speed, the selection of nose shape is thought to be the most crucial. The aerodynamic bodies traveling at supersonic speeds experience a pronounced influence of fluid compressibility, wherein high-speed fluid particles impart their kinetic energy as heat upon interacting with the frontal surface. The primary difficulty is that missiles and aerodynamic vehicles with high aerodynamic loads depend heavily on the shape of their noses. Therefore, the purpose of this research work is to compare the shape of the wedge and the conical nose at Mach number 2.0. A numerical simulation is used to estimate aerodynamic properties such as downstream Mach number, shock wave angle, pressure ratio, density ratio, temperature ratio, and aerodynamic coefficient, and the results are compared with theoretical results, which are obtained to solve oblique shock relation and Taylor–Maccoll equation. The conical-shaped nose model exhibits superior aerodynamic characteristics compared to the wedged-shaped nose. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of Numerical Heat Transfer: Part A -- Applications is the property of Taylor & Francis Ltd and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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RecordInfo BibRecord:
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    Identifiers:
      – Type: doi
        Value: 10.1080/10407782.2024.2328764
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      – Code: eng
        Text: English
    PhysicalDescription:
      Pagination:
        PageCount: 25
        StartPage: 5329
    Subjects:
      – SubjectFull: Mach number
        Type: general
      – SubjectFull: Compressibility (Fluids)
        Type: general
      – SubjectFull: Aerodynamic load
        Type: general
      – SubjectFull: Kinetic energy
        Type: general
      – SubjectFull: Projectiles
        Type: general
      – SubjectFull: Shock waves
        Type: general
    Titles:
      – TitleFull: Theoretical and numerical investigation of wedge and cone nose profiles at supersonic speed.
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            NameFull: Kumar, Uttam
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            NameFull: Kumar, Rakesh
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          Dates:
            – D: 01
              M: 08
              Text: 2025
              Type: published
              Y: 2025
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              Value: 86
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              Value: 15
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            – TitleFull: Numerical Heat Transfer: Part A -- Applications
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