Publications
Studium obliczeniowe aerodynamiki samolotu przydźwiękowego o dużej manewrowości (Computational study of super-maneuverability transonic aircaft)
Ł. Mazurkiewicz, K. Kubryński. Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej - Mechanika w Lotnictwie XVI 2014
The paper presents results of computational analysis of the flow around the initial configuration of the aircraft, for which the main objective is to ensure good aerodynamic characteristics at high angles of attack. It is assumed that the basic aerodynamic design and verification of characteristics for the case of low speeds and high angles of attack is based on the low speed wind tunnel tests. The basic tool for the design and analysis of aerodynamic characteristics at high speeds (transonic and low supersonic) are computational methods. The paper presents computational results for two cases: the Mach number of 0.3 and the full range of angles of attack (up to 90 deg) and for angles of attack in the range of 0.5-7 deg and Mach numbers up to 1.05. Characteristics of lift and drag as well as characteristics of stability and control and, additionally, total pressure losses in the engine inlet duct are analysed. The work is a preliminary study of the highly maneuverable transonic aircraft.
CFD analysis of AT-6 aircraft
Ł. Mazurkiewicz. Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej - Mechanika w Lotnictwie XVI 2014
During the design phase of the new AT-6 aircraft, computational numerical methods for fluid dynamics (CFD) have been applied to determine the basic aerodynamic characteristics. The analyzes have allowed one to find flow separation and capture the negative impact of the canard wake and tip vortex interference in an early stage of the project. As a result geometry have been modified to improve the aerodynamic characteristics and minimize the negative effect of the aerodynamic interference. The paper presents a comparison of the flow and characteristics before and after modifications.
Analiza przepływu i modernizacja tunelu niskiej turbulencji (Low turbulence wind tunnel modernization and flow analysis)
Ł. Mazurkiewicz, K. Kubryński, R. Jóźwiak. Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej - Mechanika w Lotnictwie XVI 2014
The paper describes the modernization of low-turbulence wind tunnel located in Aerodynamic Laboratory, Warsaw University of Technology, the Faculty of Power and Aeronautical Engineering. The aim is to obtain a fully functional tunnel for 2D airfoils testing. The modernization covered the tunnel circuit, settling chamber, the test section, fan, cooling system, but also the development and implementation of the control system, measurement, data acquisition and processing of test results-including calibration of the tunnel. The effect of these changes is a significant improvement of research capacity of the tunnel, but also new experience regarding principles of the wind tunnel design. It was utilized in the new, larger wind-tunnel project.
Optymalizacja układu powierzchni nośnych samolotu ze skrzydłem smukłym i niekonwencjonalnym usterzeniem pionowym (Optimization of lifting surfaces geometry for a slender-wing aircraft with non-conventional vertical tail)
Ł. Mazurkiewicz. Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej - Mechanika w Lotnictwie XII 2006
Modern combat and training aircraft operate withing a wide range of angles of attack (AoA). However, some problems arise with lateral-directional stability and controllability (becoming particularly difficult to cope the range of 30-40 deg of AoA) main causes of which consist in: flow separation on the wing surfaces, the effect of strong vortex flows generated on the fuselage, strakes and interaction with vertical tail. A possible solution to this problem consist in application of a twin fin tail with a small sweep angle, which improves directional stability characteristics, poses however some other problems (structure vibrations).
In the paper a new concept of solving the problem is presented. That means - no classic vertical tail has been introduced into the proposed aircraft configuration. The directional stability is ensured by means of introduction of small surfaces of a high sweep angle on the bottom surface of each wing and assuming a proper fuselage nose geometry. Such a solution eliminates undesirable interactions between vortices and vertical tail surfaces. At small and moderate AoA this configuration makes it possible to reduce the induced drag and as a results provides the opportunity for increasing the aerodynamic efficiency. The optimization process of lifting surfaces, as well the results of numerical analysis and wind tunnel test are also presented.
Nowa koncepcja układu samolotu dla dużych kątów natarcia (The new concept of high maneuverability aircraft)
Ł. Mazurkiewicz, K. Kubryński. Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej - Mechanika w Lotnictwie XI 2004
Nowa koncepcja układu samolotu dla dużych kątów natarcia (The new concept of high maneuverability aircraft)
Ł. Mazurkiewicz, K. Kubryński. Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej - Mechanika w Lotnictwie XI 2004