Effect of sweptback angle of a delta wing on surface pressure distribution at supersonic Mach numbers

Shetty, Shamitha and Crasta, Asha and Khan, Sher Afghan and Aabid, Abdul and Baig, Muneer (2024) Effect of sweptback angle of a delta wing on surface pressure distribution at supersonic Mach numbers. Fluid Dynamics and Material Processing, 20 (10). pp. 2353-2376. ISSN 1555-256X E-ISSN 1555-2578

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Abstract

This work aims 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.

Item Type:	Article (Journal)
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics
Kulliyyahs/Centres/Divisions/Institutes (Can select more than one option. Press CONTROL button):	Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User:	Prof. Dr. Sher Afghan Khan
Date Deposited:	26 Sep 2024 11:14
Last Modified:	26 Sep 2024 12:36
URI:	http://irep.iium.edu.my/id/eprint/114665

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