Numerical analysis of the influence of particular autogyro parts on the aerodynamic forces

¹ Lublin University of Technology, Faculty of Mechanical Engineering, Department of Thermodynamics, Fluid Mechanics and Aviation Propulsion Systems, Nadbystrzycka 36 Str., 20-618 Lublin, poland
² Polish Air Force Academy, Department of Airframe and Engine, 35 Dywizjonu 303 Str., 08-521 Dęblin, poland
³ Institute of Aviation, Aerodynamics Department, Krakowska 110/114, 02-256 Warsaw, poland

^* Corresponding author: z.czyz@pollub.pl

Abstract

This paper describes the research gyrocopter and presents the methodology of numerical calculations for this type of research objects. There are also the results of an ANSYS Fluent three-dimensional simulation of an airflow around a gyrocopter, excluding an airflow around its main rotor and propeller blades. The calculations enabled basic aerodynamic characteristics. The analysis of the numerical calculations focuses on the impact of gyrocopter individual sections like a fuselage, tail, tail boom, etc., on aerodynamic forces and moments, as well as coefficients of aerodynamic forces and moments. The research scope covers an angle of attack α ranging between -20° and 25° at a sideslip angle equal to 0.