LIFT OF SLENDER DELTA WINGS ACCORDING TO NEWTONIAN THEORY
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Publication:5723765
DOI10.2514/3.1644zbMath0115.20704OpenAlexW2015575302MaRDI QIDQ5723765
Publication date: 1963
Published in: AIAA Journal (Search for Journal in Brave)
Full work available at URL: http://hdl.handle.net/2027.42/77552
Related Items (16)
Hypersonic flow past a wing at large angles of attack with detached shock wave ⋮ Optimum lifting body shapes in hypersonic flow at high angles of attack ⋮ Processing of gasdynamic numerical solutions in similarity parameters ⋮ Hypersonic flow past conical V-shaped wings ⋮ Lifting wings of optimum shape in a viscous hypersonic stream ⋮ Stability of an hypersonic magnetohydrodynamic shock wave ⋮ Hypersonic flow of gas over a slender wing of variable shape ⋮ On the theory of a wing with small aspect ratio in a hypersonic flow ⋮ Nonequilibrium hypersonic flow of gas past a wing of small aspect ratio ⋮ Singularities of the flow field in the neighborhood of the windward surface of a small aspect ratio delta wing in hypersonic stream ⋮ An inviscid analysis of swept oblique shock reflections ⋮ Hypersonic flow past a delta wing ⋮ Optimization of the shape of a wing in a hypersonic nonequilibrium gas flow ⋮ Hypersonic flow past a delta wing at large angles of attack ⋮ Aerodynamic characteristics of \(V\)-shaped wings with shock waves detached from leading edges at hypersonic speeds ⋮ Three-dimensional hypersonic gas flow over wings
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