Numerical and Experimental Investigation of Aerodynamics Characteristics of NACA 0015 Aerofoil

Abstract

Abstract-An aerofoil is a streamline body. Symmetric aerofoil (NACA 0015) is used in many applications such as in aircraft submarine fins, rotary and some fixed wings. The ultimate objective of an aerofoil is to obtain the lift necessary to keep an airplane in the air. But construction of the blade with proper angle of attack and implementation has significant effect on lift force. Insufficient lift force might cause fail of airplane flying, especially at high speed. Modern technologists use different simulation techniques to avoid costly model testing. But simulation is based on some assumption. Thus practically results are not fully authentic and have a deviation. In this work numerical and experimental investigation of NACA 0015 is studied at different angle of attack (degree) at different velocity of air by determining the forces at every two degrees from 0 0 to 18 0 . The experiment is conveyed in a low speed wind tunnel. The numerical analysis is conducted using ANSYS (combined with CFD and FLUENT FLOW). The use of the CFD technology greatly reduces the overall investment and efforts for aerofoil design. CFD method contributes to visualize the flow pattern inside aerofoil and takes less time and comparatively faster than experiment. After completing the experimental, numerical data is compared. Therefore, the objective of this paper is to find the deviation and validation of aerodynamics characteristics of NACA 0015 aerofoil for experimental and numerical method.

Use of Karl Fischer titration for the localized measurement of water content in FRP composite aircraft parts removed from service

“…Furthermore, several authors have shown that, depending on the blades' angle of attack and their shape, the contours of static pressure and the contours of velocity magnitude around the NACA airfoil evolve. 84,85 Depending on its position and angle, these pressure differences along the blade should impact the air flows and damage caused.…”

Determination of parameters affecting aerodynamic performance in S833 airfoil

“…As the current on the airfoils is often close to twodimensional, it is sufficient to examine the flow properties around the flow around a single cross-section as the flow characteristics remain the same in all sections along the airfoil [20]. Airfoil cross-sectional geometry is shown in Fig.…”

“…The drag force depends on both the pressure and friction distribution along the surface. Because of the different shapes and dimensions of the airfoils developed for various purposes, dimensionless coefficients are taken into consideration in the comparisons and evaluations [20]. C L eq.…”

“…Other terms in the equation are L (the L lift force), D (the D drag force), V (the V wind speed), ρ (the ρ fluid density), S (the S airfoil surface area). After calculating these coefficients without dimension, the C L /C D ratio can be used practically for performance comparisons [20].…”

Sesaltı Rüzgar Tünelinde Kanat Aerodinamiği Kuvvet Ve Akış Görüntüleme Analizleri

“…Reynolds sayı kaldırma katsayısının artmasıyla biraz artar ve belli bir noktadan sonra azalır. Azaldığı kısımda kanat profili üzerinde büyük negatif basınç oluşmaktadır (Rubel, Uddin, Islam, & Rokunuzzaman, 2016) Rüzgâr tünelinde yapılacak olan deneysel çalışmaların başlangıcı literatürde değerleri bulunan bir kanat profili ile yapılması düşünülmüştür. NACA0015 kanat profili imal edilmesi ve literatür karşılaştırılması bakımından tercih edilmiştir.…”