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- W2020161657 abstract "The present study aims at relating lift and drag to flow structures around a delta wing of elliptic section. Aerodynamic forces are analysed in terms of fluid elements of non-zero vorticity and density gradient. The flow regime considered is M α = 0.6 ∼ 1.8 and α = 5° ∼ 19°, where M α denotes the free-stream Mach number and α the angle of attack. Let ρ denote the density, u velocity, and ω vorticity. It is found that there are two major source elements R e (x) and V e (x) which contribute about 95% or even more to the aerodynamic forces for all the cases under consideration, [R_e({bm x})=-frac{1}{2} {bm u}^2 nablarho cdot nablaphiquad {rm and}quad V_e ({bm x}) = -rho{bm u}times {bm omega}cdot nablaphi,] where θ is an acyclic potential, generated by the delta wing moving with unit velocity in the negative direction of the force (lift or drag). All the physical quantities are non-dimensionalized. Detailed force contributions are analysed in terms of the flow structures and the elements R e (x) and V e (x) . The source elements R e (x) and V e (x) are concentrated in the following regions: the boundary layer in front of (below) the delta wing, the primary and secondary vortices over the delta wing, and a region of expansion around the leading edge. It is shown that V e (x) due to vorticity prevails as the source of forces at relatively low Mach number, M α < 0.7. Above about M α = 0.75, R e (x) due to compressibility generally becomes the dominating contributor to the lift, while the overall contribution from V e (x) decreases with increasing M α , and even becomes negative at M α = 1.2 for the lift, and at a higher M α for the drag. The analysis is carried out with the aid of detailed numerical results by solving the Reynolds-averaged Navier–Stokes equations, which are in close agreement with experiments in comparisons of the surface pressure distributions." @default.
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- W2020161657 date "1996-06-10" @default.
- W2020161657 modified "2023-09-25" @default.
- W2020161657 title "An analysis of aerodynamic forces on a delta wing" @default.
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- W2020161657 doi "https://doi.org/10.1017/s0022112096000493" @default.
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