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4 Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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Numerical and experimental aerodynamic optimisation of two-seated light aircraft

Stalewski W., Wysocki Z.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2001

nr 12

79-84

This paper presents a numerical and experimental optimisation of the two-seated A S-2 aircraft. In the numerical part of study, geometrical modifications and the flow field analysis of some selected regions of the aircraft i.e. cockpit-wings, cockpit - rear part of the fuselage were performed. The wind tunnel experiments of initial and modified versions of the aircraft model were made, too. The balance measurements and tufts flow visualisation was conducted as well.

Light airplane design philosophy in the Institute of Aviation - past, present and future

Piwek K.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2001

nr 12

53-62

The paper presents the design activity of the Institute of Aviation that was founded in 1926 to develop, and test aeronautical engineering products. The survey comprises : a report from 1930, the main milestones, such as experimental helicopter, a family of trainers (Bies, Iskra, and Iryda), research capabilities, and the current task of the Institute of Aviation, i.e. to create a scientific basis for aeronautical engineering tailored to the market economy. As a result, the military industrial complex is adopted for civil applications, thus creating a general aviation program. The primary objective of the paper is to show: where the Polish aviation is now, the trends in aviation development in other countries (AGATE - program), and the ways Poland can make impact on world aviation.

Computational analysis of longitudinal dynamic stability for very light airplane

Danek V.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2000

nr 10

83-88

A linearized analytic model of general longitudinal movement of airplane is discussed. Linearized deviation equations of motion, derived in stability axes system, are applied to the parametric analysis of airplane's longitudinal dynamic stability under arbitrary symmetric flight conditions. The analytic model is generated in the form of inter-active software package PODYST_ALFA. This is used to show the influence of some constructional and mass parameters on the longitudinal airplane motions after encountering disturbance for a chosen steady level flight.

Modelling of a light aircraft asymmetrical touchdown

Błaszczyk P.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

1998

nr 8

65-68

Main objective of this paper is to develop the mathematical model and to find the aircraft landing characteristics from the numerical simulation. The asymmetrical touchdown is considered. The full, light aircraft dynamics in-flight model including gear and tire models will be presented. The equations of motions are obtained from the balance of momentum theorem and the balance of the moment of momentum theorem. Aerodynamic forces are determined basing on linear quasi-stationary aerodynamics model. Tire forces and moments are described by linear algebraic equations for stationary, and by linear differential equations for nonstationary model. Various stationary and nonstationary massless tire models are described. The presented mathematical model of aircraft can be used to calculate continuous time histories during the aircraft asymmetrical touchdown and also finding the stability of taxiing.