Numerical Investigation of Viscous Laminar Supersonic Flow Past an Asymmetric Biconvex Circular-Arc Aerofoil

Abstract:

A numerical investigation of two-dimensional unsteady, viscous and laminar compressible flow past an asymmetric biconvex circular-arc aerofoil in supersonic regime is carried out. The focus of the present work is to investigate the effects of variation of Mach number, at two different angles of attack, on the flow and force characteristics on NACA 2S-(50)(04)-(50)(20) aerofoil. The value of Reynolds number is taken as 5x10⁵. The computations are carried out at Mach numbers of 1.25, 1.5 and 2.0 at an angle of attack of α=0° and α=10°. It is found that the aerofoil works well in the supersonic flow and, unlike the conventional symmetric biconvex aerofoil, generates finite lift at α=0° due to stronger shock waves at the lower surface. Moreover, the L/D ratio at α=10° is always found to be more than 2.5.

• Periodical: Applied Mechanics and Materials (Volume 390)
• Pages: 147-151
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.390.147
• Online since: August 2013
• Authors: Saif Akram, Nadeem Hasan, Aqib Khan
• Keywords: Asymmetric Biconvex Circular-Arc Aerofoil, Compressible Flow, Laminar, Viscous

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