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Dr. Pericles Panagiotou
Aristotle University of Thessaloniki

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0 Aerodynamics
0 Aircraft Design
0 Fluid Dynamics
0 Fluid Mechanics
0 Turbulence

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Journal article
Published: 06 January 2021 in Aerospace
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The current study presents a low-fidelity, quasi-3D aerodynamic analysis method for Blended-Wing-Body (BWB) Unmanned Aerial Vehicle (UAV) configurations. A tactical BWB UAV experimental prototype is used as a reference platform. The method utilizes 2D panel method analyses and theoretical aerodynamic calculations to rapidly compute lift and pitching moment coefficients. The philosophy and the underlying theoretical and semi-empirical equations of the proposed method are extensively described. Corrections related to control surfaces deflection and ground effect are also suggested, so that the BWB pitching stability and trimming calculations can be supported. The method is validated against low-fidelity 3D aerodynamic analysis methods and high-fidelity, Computational Fluid Dynamics (CFD) results for various BWB configurations. The validation procedures show that the proposed method is considerably more accurate than existing low-fidelity ones, can provide predictions for both lift and pitching moment coefficients and requires far less computational resources and time when compared to CFD modeling. Hence, it can serve as a valuable aerodynamics and stability analysis tool for BWB UAV configurations.

ACS Style

Pericles Panagiotou; Thomas Dimopoulos; Stylianos Dimitriou; Kyros Yakinthos. Quasi-3D Aerodynamic Analysis Method for Blended-Wing-Body UAV Configurations. Aerospace 2021, 8, 13 .

AMA Style

Pericles Panagiotou, Thomas Dimopoulos, Stylianos Dimitriou, Kyros Yakinthos. Quasi-3D Aerodynamic Analysis Method for Blended-Wing-Body UAV Configurations. Aerospace. 2021; 8 (1):13.

Chicago/Turabian Style

Pericles Panagiotou; Thomas Dimopoulos; Stylianos Dimitriou; Kyros Yakinthos. 2021. "Quasi-3D Aerodynamic Analysis Method for Blended-Wing-Body UAV Configurations." Aerospace 8, no. 1: 13.

Journal article
Published: 01 November 2017 in Aerospace
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An experimental investigation of the wake of an Unmanned Aerial Vehicle (UAV) model using flow visualization techniques and a 3D Laser Doppler Anemometry (LDA) system is presented in this work. Emphasis is given on the flow field at the wingtip and the investigation of the tip vortices. A comparison of the velocity field is made with and without winglet devices installed at the wingtips. The experiments are carried out in a closed-circuit subsonic wind tunnel. The flow visualization techniques include smoke-wire and smoke-probe experiments to identify the flow phenomena, whereas for accurately measuring the velocity field point measurements are conducted using the LDA system. Apart from the measured velocities, vorticity and circulation quantities are also calculated and compared for the two cases. The results help to provide a more detailed view of the flow field around the UAV and indicate the winglets’ significant contribution to the deconstruction of wing-tip vortex structures.

ACS Style

Pericles Panagiotou; George Ioannidis; Ioannis Tzivinikos; Kyros Yakinthos. Experimental Investigation of the Wake and the Wingtip Vortices of a UAV Model. Aerospace 2017, 4, 53 .

AMA Style

Pericles Panagiotou, George Ioannidis, Ioannis Tzivinikos, Kyros Yakinthos. Experimental Investigation of the Wake and the Wingtip Vortices of a UAV Model. Aerospace. 2017; 4 (4):53.

Chicago/Turabian Style

Pericles Panagiotou; George Ioannidis; Ioannis Tzivinikos; Kyros Yakinthos. 2017. "Experimental Investigation of the Wake and the Wingtip Vortices of a UAV Model." Aerospace 4, no. 4: 53.