Aerodynamic characteristics of multi-surface aircraft configurations

Abstract

This paper describes the wind tunnel testing of a specially designed aircraft model allowing systematic variation of geometric parameters related to overall aircraft configurations. The experiment work was carried out in the 1.8 m low-speed wind tunnel at VZLU, Aeronautical Research and Test Institute in Prague. The resultant data created an aerodynamic database for numerical modelling and verification. In addition, numerical validation of CFD package FLUENT was performed in the computerised fluid dynamic laboratory at the Department of Aerospace Engineering, University of Glasgow as a part of the ongoing research collaboration between both institutions. The wind-tunnel test program had two aims

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  to provide basic aerodynamic data effects of multi-surface aircraft configurations with a view to assessing the degree to which specific design features such as a combination of canard, wing and tail plane are beneficial to aircraft aerodynamic performance

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  to provide an aerodynamic database for numerical validation.

The aerodynamic data for different geometrical aircraft configurations with the same wing, fuselage, horizontal tail and canard surfaces were compared. The results show the magnitude of lift, drag and pitching moment depending on the angle of attack and various positions of canard, wing and horizontal tail with respect to one another. They have been compared with studied references. The experimental results are in accordance with theoretical predictions.