2026· MATEC Web of Conferences· 0 citations· 10 references
Abstract
This article analyzes the aerodynamic characteristics of the NACA2412 and NACA23012 airfoils under low angles of attack. Computational fluid dynamics (CFD) numerical simulation is used to design geometric models and perform mesh generation, while the data were analyzed using a finite element method to calculate lift and drag coefficients for both airfoils. A solver based on pressure along with a turbulence model of K - ω SST in this analysis. Here are the results: at angles of attack from 0 to 12 degrees, basically pressure difference between upper and lower surfaces making a big difference on the lift. The maximum
CL/CD
for both airfoils is also found from 8 to 10 degrees angles of attack. However, the NACA2412 generally has higher lift-to-drag ratio, lift coefficient and drag coefficient compared to the NACA23012 which means better performance in flight missions. Since most of the aircraft's transport missions spend the main time in the stratosphere, this study will be beneficial for researching the choice of using NACA2412 and NACA23012 when the airflow is smooth.
To clarify the aerodynamic performance boundaries and applicable scenarios of the classic four-digit NACA airfoil under high-Reynolds-number conditions, this paper takes the NACA2412 cambered airfoil and the NACA0012 symmetrical airfoil as the research objects. Using the fluid mechanics numerical simulation method and...
Shao-Hao Yang· MATEC Web of Conferences· 0 citations
In this paper, aerodynamic performance of three NACA airfoils, including NACA 2412, NACA 4412, and NACA 0012 are examined in two-dimensional CFD simulation to compare their aerodynamic performance. The current simulation is conducted at Re = 1.0 × 10
5
with turbulence model is able to predict adverse pressure gradi...
Congxiang Xue· MATEC Web of Conferences· 0 citations
This paper conducts two-dimensional numerical simulation experiments on NACA0012 and NACA2412 wing profiles, using a two-dimensional coordinate system to simulate wing profile data and generate structured grid computing domains and aircraft wing profile meshes centered around the wing profile. Computer simulation softw...
Wenhao Zhao· MATEC Web of Conferences· 0 citations
Winglets are aerodynamic devices that reduce induced drag by mitigating wingtip vortices, thereby improving aircraft fuel efficiency and overall performance. This study presents a comparative computational investigation of the aerodynamic performance of wings with NACA 2412 (cambered) and NACA 0012 (symmetric) airfoils...
Irfan Nazir Wani, Manoj Kumar, P. Shukla· Discover Vehicles· 0 citations
This study examines the aerodynamic performance of airfoils using numerical simulations. It compares pressure distributions, velocity profiles, and lift and drag coefficients of two airfoils, one is symmetric and another is cambered. The cambered airfoil produces higher lift due to increased pressure gradients near th...
Muddachsir Rahman, Z. Bangalee· Dhaka University Journal of...· 0 citations
The paper discusses the behavior of two popular airfoils in the same conditions of flow, which are NACA 4412 and NACA 6412, at a Reynolds number of 1.85 ×10⁶, and uses computational fluid dynamics (CFD) as its primary instrument. The alteration in the flow field is considered also since the angle of attack is increased...
Jiawei Wang· MATEC Web of Conferences· 0 citations
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