Control of flow structure on low swept delta wing with staedy leading edge blowing

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Date

2014

Author

Zharfa, Mohammadreza

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Unmanned Combat Air Vehicles (UCAVs), Unmanned Air Vehicles (UAVs) and Micro Air Vehicles are becoming extremely popular due to introducing many advantages to defense industry and aeronautical field. In line with this, the aerodynamics of these vehicles, which can be represented by simplified planforms, including delta wings, have been of considerable interest in recent years. This interest has stimulated investigation of the flow structure, as well as its control, on delta wings having low and moderate values of sweep angle. In the present study, the flow structure is characterized on a delta wing of low sweep 35° angle, which is subjected to steady leading edge blowing. The techniques of laser illuminated smoke visualization, laser Doppler anemometry (LDA), and surface pressure measurements are employed to investigate the steady and unsteady nature of the flow structure on delta wing, in relation to wing attack angle and Reynolds number. Using statistics and spectral analysis, unsteadiness of the flow structure is studied in detail. Computer controlled air injection system is designed and applied to the delta wing used in flow characterization. Effect of steady blowing through the leading edges of the wing on flow structure is studied to delay or to prevent three-dimensional surface separation and possibly to reduce the buffeting on the wing surface. Effective blowing coefficient ranges for flow control are determined.

Subject Keywords

Airplanes, Leading edges (Aerodynamics)., Vortex-motion., Flow visualization., Fluid dynamics.

URI

http://etd.lib.metu.edu.tr/upload/12618382/index.pdf
https://hdl.handle.net/11511/24361

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Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

M. Zharfa, “Control of flow structure on low swept delta wing with staedy leading edge blowing,” M.S. - Master of Science, Middle East Technical University, 2014.