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Longitudinal stability characteristics of the LASTA airplane

Miodrag Milenković-Babić (Military Technical Institute, Belgrade, Serbia)
Marija Samardžić (Military Technical Institute, Belgrade, Serbia)
Vuk Antonić (Military Technical Institute, Belgrade, Serbia)
Milica Marjanović (Military Technical Institute, Belgrade, Serbia)
Vanja Stefanović-Gobeljić (Military Technical Institute, Belgrade, Serbia)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 2 October 2017

380

Abstract

Purpose

This paper presents the longitudinal stability analysis of a single tractor propeller airplane LASTA at high engine power settings. This analysis is part of the ongoing process of certifying the airplane for civil use according to the civil regulations CS-23.

Design/methodology/approach

The design methodology that is presented in the paper consists of comparing flight test aerodynamic and calculation results. The methods used here are standard and routinely used in flight testing.

Findings

Flight testing results indicate that at low airspeeds the cumulative destabilizing effects because of high values of the angle of attack and high power settings are about 6 per cent of MAC. This value is in a very good agreement with published data.

Practical implications

The information presented in this paper are new, and are very specific to this one aircraft configuration. The methods used here are standard and widely used in flight testing.

Originality/value

The information in this paper presents flight test results. There are not many publications in this area.

Keywords

Acknowledgements

The authors express sincere gratitude to the colleagues from the Military Technical Institute (VTI), Belgrade, and the Technical Testing Centre, Belgrade, for their assistance, helping at each stage of the work process and support.

Citation

Milenković-Babić, M., Samardžić, M., Antonić, V., Marjanović, M. and Stefanović-Gobeljić, V. (2017), "Longitudinal stability characteristics of the LASTA airplane", Aircraft Engineering and Aerospace Technology, Vol. 89 No. 6, pp. 911-919. https://doi.org/10.1108/AEAT-02-2016-0026

Publisher

:

Emerald Publishing Limited

Copyright © 2017, Emerald Publishing Limited

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