Investigation of pressure and temperature distributions in aerofoils using CFD simulation

Ramesh KRISHNAN L; Jasgurpreet Singh CHOHAN; S. VIJAYAKUMAR; N.  BEEMKUMAR; Sriram DESIKAN; V Nagabhushana RAO; M.Naga Swapna SRI; Mayank KUNDLAS

doi:10.55713/jmmm.v35i2.2213

Authors

Ramesh KRISHNAN L Department of Mechanical Engineering, KCG College of Technology, Karapakkam, Chennai-97
Jasgurpreet Singh CHOHAN University School of Mechanical Engineering, Rayat Bahra University, Kharar, Punjab 140103, India; Faculty of Engineering, Sohar University, PO Box 44, Sohar, PCI 311, Oman
S. VIJAYAKUMAR Department of Mechanical Engineering, Graphic Era Hill University, Dehradun-248002, Uttarakhand, India; Department of Mechanical Engineering, Graphic Era Deemed to be University, Dehradun-248002, Uttarakhand, India
N. BEEMKUMAR Department of Mechanical Engineering, School of Engineering and Technology, JAIN (Deemed to be University), Bangalore, Karnataka, India
Sriram DESIKAN Department of Mechanical Engineering, Indra Ganesan College of Engineering, Trichy, Tamil Nadu
V Nagabhushana RAO Department of Mechanical Engineering,Raghu Engineering College, Visakhapatnam, Andhra Pradesh-531162, India
M.Naga Swapna SRI Department of Mechanical Engineering,P V P Siddhartha Institute of Technology, Vijayawada
Mayank KUNDLAS Centre for Research Impact & Outcome, Chitkara University Institute of Engineering and Technology, Chitkara University, Rajpura, 140401, Punjab, India

DOI:

https://doi.org/10.55713/jmmm.v35i2.2213

Keywords:

Aerofoil, M13, Eppler 1233, Computational, Pressure co efficient

Abstract

Most aircraft derive the design of their wings, fins, and horizontal stabilizers from this construction approach, incorporating curved surfaces to enhance the lift-to-drag ratio during flight. Over the past decade, Computational Fluid Dynamics (CFD) has become the leading tool for designing components and processes involving fluid or gas movement across industries such as aviation, automotive, and manufacturing. This study examines the aerodynamic characteristics—including pressure, density, and temperature distribution, as well as lift and drag forces—of two different angles of attack based on the M13 and Eppler 1233 airfoils. The analysis considers an airfoil with varying chord thickness while maintaining a consistent maximum thickness as a percentage of the chord length. The primary objective of this research is to conduct a comprehensive numerical assessment of airfoil structures. A 2D computational simulation is performed on different airfoil shapes at angles of attack of 0° and 8° using ANSYS Fluent. The results reveal variations in flow characteristics across different structures and evaluate the balance between lift and drag forces at various angles of attack to enhance aerodynamic efficiency. According to the study, aerodynamic performance and stability are both enhanced when aerofoil designs are optimised to reduce turbulence and flow separation. This exemplifies the compromise that must be made to maximise aerodynamic performance by either increasing lift or controlling drag. The findings contribute to a deeperunderstanding of airflow over airfoil structures and its impact on aircraft performance.

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