An Investigation of Flow Fluids Over Multi-Element Aerofoils  

Oleh:

Bruun, H. H. ; Maddah, S. R.

Jenis: Article from Bulletin/Magazine
Dalam koleksi: Journal of Fluids Engineering vol. 124 no. 1 (2002), page 154-165.
Topik: Elements; investigation; flow fluids; multi - element; aerofoils

Ketersediaan

Perpustakaan Pusat (Semanggi) Nomor Panggil: JJ89.4 Non-tandon: 1 (dapat dipinjam: 0) Tandon: tidak ada

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Isi artikel

This paper presents results obtained from a combined experimental and computational study of the flow field over a multi - element aerofoil with and without an advanced slat. Detailed measurements of the mean flow and turbulent quantities over a multi - element aerofoil model in a wind tunnel have been carried out using stationary and flying hot - wire (FHW) probes. The model configuration which spans the test section (600 mm × 600 mm), is made of three parts : 1) an advanced (heel - less) slat, 2) a NACA 4412 main aerofoil and 3) a NACA 4415 flap. The chord lengths of the elements were 38, 250 and 83 mm, respectively. The results were obtained at a chord Reynolds number of 3 × 10(5) and a free Mach number of less than 0.1. The variations in the flow field are explained with reference to three distinct flow field regimes : attached flow, intermittent separated flow, and separated flow. Initial comparative results are presented for the single main aerofoil and the main aerofoil with a non deflected flap at angles of attacks of 5, 10, and 15 deg. This is followed by the results for the three - element aerofoil with emphasis on the slat performance at angles of attack L = 10, 15, 20, and 25 deg. Results are discussed both for a non deflected flap (d(f) = 0 deg) and a deflected flap (d(f) = 25 deg). The measurements presented are combined with other related aerofoil measurements to explain the main interaction of the slat / main aerofoil and main aerofoil / flap both for nondeflected and deflected flap conditions. These results are linked to numerically calculated variations in lift and drag coefficients with angle of attack and flap deflection angle.

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