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madani, A., Djavareshkian, M., KARIMI KELAYEH, R. (2022). Optimization of split drag rudder mechanism at different angles of attack in a flying wing airplane. Electronic and Cyber Defense, 11(1), 1-16.
afshin madani; Mohammad Hassan Djavareshkian; Ruhollah KARIMI KELAYEH. "Optimization of split drag rudder mechanism at different angles of attack in a flying wing airplane". Electronic and Cyber Defense, 11, 1, 2022, 1-16.
madani, A., Djavareshkian, M., KARIMI KELAYEH, R. (2022). 'Optimization of split drag rudder mechanism at different angles of attack in a flying wing airplane', Electronic and Cyber Defense, 11(1), pp. 1-16.
madani, A., Djavareshkian, M., KARIMI KELAYEH, R. Optimization of split drag rudder mechanism at different angles of attack in a flying wing airplane. Electronic and Cyber Defense, 2022; 11(1): 1-16.

Optimization of split drag rudder mechanism at different angles of attack in a flying wing airplane

مکانیک سیالات و آیرودینامیک
Article 1, Volume 11, Issue 1 - Serial Number 29, October 2022, Pages 1-16    PDF (3.33 M)
Document Type: Original Article
Authors
afshin madani1; Mohammad Hassan Djavareshkian* 2; Ruhollah KARIMI KELAYEH3
1Master student of Ferdowsi University of Mashhad, Faculty of Engineering, Mashhad, Iran
2Professor, Faculty of Engineering Ferdowsi University of Mashhad, Mashhad, Iran
3Master's degree, Faculty of Engineering, Ferdowsi University of Mashhad, Mashhad, Iran
Receive Date: 22 February 2022,  Revise Date: 10 June 2022,  Accept Date: 09 July 2022 
Abstract
In this research, the split drag system at different AOA for a flying wing aircraft has been simulated and optimized by a numerical method. The split drag system provides vertical axis control by creating asymmetric drag between the right and left wings. The aircraft under study is a lambda shape aircraft with a swept-back angle of 56. The split drag control system is made up of two surfaces on top of each other, by opening in the opposite direction on one side of the aircraft, it creates the drag necessary to produce yawing moment. Their installation position is at the tip of the wings and on the trailing edge. When using split drag, in addition to the yawing moment, a disturbing rolling moment is created, which is caused by the drag difference between the upper and lower surface of this system, and the reason for this is the change in the AOA of the aircraft. Asymmetric opening of the surfaces can reduce the induced roll to zero and in some cases to a minimum. The test was carried out in AOA of 0 to 12ᵒ for drag split opening angles of 10, 20, and 30ᵒ. Calculations based on equations (RANS) are discretized with the finite volume method. The obtained results show how much to add to the angle of the split drag surfaces depending on the AOA in order to find the most optimal mode to neutralize the roll, and finally, the optimized diagrams of this system are obtained.
Keywords
split drag rudder; UAV; flying wing; Optimization; Numerical simulation
References

 

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