Flow Analysis of an Aircraft that Utilizes Propulsive Aerofoil Technology J. Haroon Ahmed Khan 1 , Maroju Sunanda Rajan 2 , M. Abdul Viqer 3 , K. Maruthupandiyan 4 , D. Govardhan 5 Research Student 1 , Research Student 2 , Research Student 3 , Associate Professor 4 , Head of the Department 5 , Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Telangana, India Abstract: The purpose of our Paper is to explain the Aerodynamic characteristics of an Aircraft that has an Aerofoil Shaped Fuselage. The proposed Aerofoil Shaped Fuselage although has been proven to provide better aerodynamic characteristics than that of the conventional cylindrical shaped fuselage, it also has increased Drag. The Aerofoil shaped fuselage concept, although predominantly used in the 1960’s and 1970’s has had a steep decline in its usage in commercial and military applications. Our contribution in this field is to propose a NACA 4412 Aerofoil Fuselage Aircraft that has a Swept Back, Mid-Wing configuration with a Twin Tail by designing it in CATIA V5 and then carrying out an analysis of the Model in ANSYS FLUENT 19.2. At various angles of attack, the Lift coefficient and Drag coefficient have been found. The Aerodynamic Characteristic Plots of the Aerofoil Shaped Fuselage Aircraft that have been obtained are Residual Plot, Lift Coefficient Plot, Drag Coefficient Plot, Pressure Plot, Turbulent Kinetic Energy Plot, Velocity Vector Plot for the Complete Continuum, Velocity Vector for the Aircraft and Lift Coefficient/Drag Coefficient vs Angle of Attack Plot has been obtained. Finally, some conclusions have been drawn on the basis of the Computational results of the Design as well as the Literature Survey that has been conducted. Keyword:- Aerofoil Shaped Fuselage; NACA 4412; ANSYS FLUENT 19.2; Lift Coefficient, Drag Coefficient; Aerodynamic Characteristics; Angle of Attack. 1. INTRODUCTION Aerofoil Shaped Fuselage can minimise wing drag and structure for different flight regimes, as well as rocket re- entry, whereas a flying wing tries to improve subsonic cruise efficiency by removing non-lifting surfaces. In terms of managing adequate airworthiness, all of these flight conditions provide challenges. They were a significant research topic in the mid-1970s as an attempt to build a compact, lightweight manned aerial vehicle. The US manufactured many airfoil shaped jets as well as multiple launch vehicle that were tested over the Pacific to prove the idea. United States Military abandoned interest in this topic, and extensive research on the Launch Vehicle was halted after it became apparent that the extremely arched airframe would make fuel tankage impractical. In 1957, Dr. Alfred J. Eggers Jr. devised the lifting body idea. Hence, this paper discusses the aerodynamic characteristics of aerofoil shaped fuselage aircraft model that uses a NACA 4412 Aerofoil and recommends ways to reduce the drag, provide a propulsion system suitable for our Model as well as ways to establish the need for research and development to improve the controllability and manoeuvrability of the airplane. 2. METHODOLOGY NACA 4412 cambered aerofoil has been used for design and investigation of the aerodynamic characteristics of aerofoil shaped fuselage configuration. The Aircraft was designed by using CATIA V5. The results report has been obtained by using Computational Fluid Dynamics (CFD) software, specifically by using ANSYS FLUENT 19.2. The flow of air through the aerofoils is considered to be incompressible and subsonic. The chord length of the aerofoil has been kept 18cms.The Root to Tip length of each Wing is 50cm.The density of air has been considered ρ = 1.225 kg/m3. The thickness of the Aerofoil fuselage is 8.2 cm. The total volume of the model is 8250cm3. The free stream airflow has been kept 15 m/sec and the temperature has been considered to be 313K. The design of the model involved attention to detail via trial and error, especially for the fuselage and tail interface. The design analysis was carried out by using a mesh where the size of the element was 5mm with the frequency to be considered as 3. The results converged at 150 iterations. The plots obtained where the Residual Plot, Lift Coefficient Plot, Drag Coefficient Plot, Pressure Plot, Turbulent Kinetic Energy Plot, Velocity Vector Plot for the Complete Continuum, and Velocity Vector for the Aircraft. 3. LITERATURE REVIEW Principle Burnelli was one of several American designers to delve into the idea of the "flying wing." He constructed two aircrafts in the 1920s with massive, Aerofoil-shaped hulls that delivered a significant percentage of the plane's lift. He believed in the Lift body theory i.e. A lifting body is a type of fixed-wing aeroplane in which the body produces lift. It can indeed be regarded as a fuselage with hardly any traditional wing, in comparison to a flying wing, that is a wing with hardly any traditional fuselage. Burnelli’s findings are supported by the findings of Jahangir et al (2013) as the analysis of the Aerodynamic Nomenclature Type Aerofoil Type NACA 4412 Chord Length of Aerofoil 180mm Thickness of Fuselage 200mm Tip to Tip Length of Both Wing 1200mm Root to Tip Length of each Wing 500mm International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181 http://www.ijert.org IJERTV10IS060267 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 10 Issue 06, June-2021 657
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Flow Analysis of an Aircraft that Utilizes
Propulsive Aerofoil Technology
J. Haroon Ahmed Khan1, Maroju Sunanda Rajan2, M. Abdul Viqer3, K. Maruthupandiyan4, D. Govardhan5
Research Student1, Research Student2, Research Student3, Associate Professor4, Head of the Department5,
Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Telangana, India
Abstract: The purpose of our Paper is to explain the
Aerodynamic characteristics of an Aircraft that has an Aerofoil
Shaped Fuselage. The proposed Aerofoil Shaped Fuselage
although has been proven to provide better aerodynamic
characteristics than that of the conventional cylindrical shaped
fuselage, it also has increased Drag. The Aerofoil shaped
fuselage concept, although predominantly used in the 1960’s
and 1970’s has had a steep decline in its usage in commercial
and military applications. Our contribution in this field is to
propose a NACA 4412 Aerofoil Fuselage Aircraft that has a
Swept Back, Mid-Wing configuration with a Twin Tail by
designing it in CATIA V5 and then carrying out an analysis of
the Model in ANSYS FLUENT 19.2. At various angles of
attack, the Lift coefficient and Drag coefficient have been
found. The Aerodynamic Characteristic Plots of the Aerofoil
Shaped Fuselage Aircraft that have been obtained are Residual