Open Access

ARTICLE

Effect of Sweptback Angle of a Delta Wing on Surface Pressure Distribution at Supersonic Mach Numbers

Shamitha Shetty^1,2, Asha Crasta¹, Sher Afghan Khan^3,*, Abdul Aabid⁴, Muneer Baig⁴

1 Mathematics Department, Mangalore Institute of Technology and Engineering, Visvesvaraya Technological University, Near Moodabidre, Mangaluru, Karnataka, 574225, India
2 Nitte Meenakshi Institute of Technology, Visvesvaraya Technological University, Bangalore, 560064, India
3 Department of Mechanical and Aerospace Engineering, Faculty of Engineering, International Islamic University Malaysia, Kuala Lumpur, 53100, Malaysia
4 Department of Engineering Management, College of Engineering Prince Sultan University, P.O. Box 66833, Riyadh, 11586, Saudi Arabia

* Corresponding Author: Sher Afghan Khan. Email:

(This article belongs to the Special Issue: Computational Fluid Dynamics: Two- and Three-dimensional fluid flow analysis over a body using commercial software)

Fluid Dynamics & Materials Processing 2024, 20(10), 2353-2376. https://doi.org/10.32604/fdmp.2024.051059

Received 26 February 2024; Accepted 25 June 2024; Issue published 23 September 2024

Abstract

The purpose of this work is to shed light on the effect of the pivot position on the surface pressure distribution over a 3D wing in different flight conditions. The study is intended to support the design and development of aerospace vehicles where stability analysis, performance optimization, and aircraft design are of primary importance. The following parameters are considered: Mach numbers (M) of 1.3, 1.8, 2.3, 2.8, 3.3, and 3.8, angle of incidence (θ) in the range from 5° to 25°, pivot position from h = 0.2 to 1. The results of the CFD numerical simulations match available analytical data, thereby providing evidence for the reliability of the used approach. The findings provide valuable insights into the relationship between the surface pressure distribution, the Mach number and the angle of incidence.

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Keywords

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