Heat flux and aerodynamics drag reduction of a hypersonic flow with the different tips of the taper spike design parabolic nose cone.
Saved in:
| Title: | Heat flux and aerodynamics drag reduction of a hypersonic flow with the different tips of the taper spike design parabolic nose cone. |
|---|---|
| Authors: | Raza, Md Shamim1 (AUTHOR) 2018rsme022@nitjsr.ac.in, Prasad, Anil Kumar1 (AUTHOR), Prasad, Laljee1 (AUTHOR), Narayan, Ashish2 (AUTHOR) |
| Source: | Numerical Heat Transfer: Part A -- Applications. 2025, Vol. 86 Issue 11, p3548-3565. 18p. |
| Subjects: | Mach number, Flow coefficient, Drag reduction, Drag coefficient, Hypersonic flow |
| Abstract: | The primary engineering challenge in the realm of supersonic aircraft design lies in the effective management of aero-heating and drag. This study delves into a numerical exploration of flow characteristics at Mach number 5.8, specifically focusing on the aerodynamic performance of actively modified the leading edge of the spike configurations. These configurations encompass bi-conic, parabolic, ogive, elliptical, spherical, and flat-tapered spikes attached to parabolic nose cones. The investigation is carried out at a zero-degree angle of attack, with a particular emphasis on their abilities to reduce aerodynamic drag, heating, and skin friction. Analysis of velocity vectors and contour geometries offers insights into flow patterns, and the presence of shock phenomena in front of the various tapered spike geometries. A comparative examination of these different tip-tapered spike designs on the parabolic nose cone reveals that the flat-tapered spike exhibits superior performance in terms of heat mitigation and reduction in aerodynamic drag. This can potentially be attributed to specific inflow and shock features near both the tip and the base of the spike on the parabolic nose cone, including aspects such as flow deceleration and the presence of strong and weak shock waves. These characteristics likely contribute to the observed reductions in both heating and aerodynamic drag. [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.) | |
| Database: | Engineering Source |
|
Full text is not displayed to guests.
Login for full access.
|
|
| FullText | Links: – Type: pdflink Text: Availability: 1 |
|---|---|
| Header | DbId: egs DbLabel: Engineering Source An: 185229247 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
| IllustrationInfo | |
| Items | – Name: Title Label: Title Group: Ti Data: Heat flux and aerodynamics drag reduction of a hypersonic flow with the different tips of the taper spike design parabolic nose cone. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Raza%2C+Md+Shamim%22">Raza, Md Shamim</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> 2018rsme022@nitjsr.ac.in</i><br /><searchLink fieldCode="AR" term="%22Prasad%2C+Anil+Kumar%22">Prasad, Anil Kumar</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Prasad%2C+Laljee%22">Prasad, Laljee</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Narayan%2C+Ashish%22">Narayan, Ashish</searchLink><relatesTo>2</relatesTo> (AUTHOR) – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Numerical+Heat+Transfer%3A+Part+A+--+Applications%22">Numerical Heat Transfer: Part A -- Applications</searchLink>. 2025, Vol. 86 Issue 11, p3548-3565. 18p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Mach+number%22">Mach number</searchLink><br /><searchLink fieldCode="DE" term="%22Flow+coefficient%22">Flow coefficient</searchLink><br /><searchLink fieldCode="DE" term="%22Drag+reduction%22">Drag reduction</searchLink><br /><searchLink fieldCode="DE" term="%22Drag+coefficient%22">Drag coefficient</searchLink><br /><searchLink fieldCode="DE" term="%22Hypersonic+flow%22">Hypersonic flow</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: The primary engineering challenge in the realm of supersonic aircraft design lies in the effective management of aero-heating and drag. This study delves into a numerical exploration of flow characteristics at Mach number 5.8, specifically focusing on the aerodynamic performance of actively modified the leading edge of the spike configurations. These configurations encompass bi-conic, parabolic, ogive, elliptical, spherical, and flat-tapered spikes attached to parabolic nose cones. The investigation is carried out at a zero-degree angle of attack, with a particular emphasis on their abilities to reduce aerodynamic drag, heating, and skin friction. Analysis of velocity vectors and contour geometries offers insights into flow patterns, and the presence of shock phenomena in front of the various tapered spike geometries. A comparative examination of these different tip-tapered spike designs on the parabolic nose cone reveals that the flat-tapered spike exhibits superior performance in terms of heat mitigation and reduction in aerodynamic drag. This can potentially be attributed to specific inflow and shock features near both the tip and the base of the spike on the parabolic nose cone, including aspects such as flow deceleration and the presence of strong and weak shock waves. These characteristics likely contribute to the observed reductions in both heating and aerodynamic drag. [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.) |
| PLink | https://search.ebscohost.com/login.aspx?direct=true&site=eds-live&db=egs&AN=185229247 |
| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1080/10407782.2024.2302080 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 18 StartPage: 3548 Subjects: – SubjectFull: Mach number Type: general – SubjectFull: Flow coefficient Type: general – SubjectFull: Drag reduction Type: general – SubjectFull: Drag coefficient Type: general – SubjectFull: Hypersonic flow Type: general Titles: – TitleFull: Heat flux and aerodynamics drag reduction of a hypersonic flow with the different tips of the taper spike design parabolic nose cone. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Raza, Md Shamim – PersonEntity: Name: NameFull: Prasad, Anil Kumar – PersonEntity: Name: NameFull: Prasad, Laljee – PersonEntity: Name: NameFull: Narayan, Ashish IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 06 Text: 2025 Type: published Y: 2025 Identifiers: – Type: issn-print Value: 10407782 Numbering: – Type: volume Value: 86 – Type: issue Value: 11 Titles: – TitleFull: Numerical Heat Transfer: Part A -- Applications Type: main |
| ResultId | 1 |
