Maneuverable aircraft lateral stability ensuring at high attack angles by differential deflection of the wing leading edge flaps

Аuthors

Golovnev A. V.^*, Tarasov A. L.^**

Air force academy named after professor N.E. Zhukovskii and Y.A. Gagarin, Voronezh, Russia

*e-mail: golovnyev@rambler.ru
**e-mail: andreyt4884@mail.ru

Abstract

The purpose of the work consists in studying the possibility of ensuring lateral stability of maneuverable aircraft at high attack angles by wing leading edge sections differential deflection with via computational experiment using detached-eddy computational experiment.

The authors used numerical experiment and analysis as methods of working.

Leading edge flaps are used on modern aircraft to provide smooth flow around wing leading edge without separation while attack angle increasing. We propose to deflect only the root sections of leading edge flaps at high values of attack angles. It will allow fixing separation over the leading edges end sections and balancing aircraft loose-flow vortex structure.

The paper carries out comparison of lateral aerodynamic performances of a maneuvering aircraft obtained by detached-eddy computational method. It presents the range of aircraft attack angles where implementation of the suggested wing leading edge sections differential structure is efficient to improve its aerodynamic performance.

The calculations were performed using the method of detached eddy simulation. Pressure fields in aircraft sections and its surface were used to analyze the flow-around structure.

The results of this work can be used by scientific and design organizations engaged in development of maneuverable aircraft aerodynamic configurations and control systems, as well as by aviation universities for educational process improvement.

It is expedient to use the suggested leading edge flaps differential configuration with attack angle values of 28–33 degrees, which will allow static transverse stability degree increase, as well as yaw angles values at which it preserves transverse and lateral stability. With this, the wing leading edge flaps differential deflection within this range leads to slight reduction of the aircraft lateral static stability reduction.

Keywords:

maneuverable aircraft, aircraft lateral aerodynamic performance, wing leading edge flaps differential deflection

References

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6. Golovnev A.V., Tarasov A.L. Nauchnyi vestnik MGTU GA, 2015, no. 218, pp. 42-49.

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