Hypersonic flow of gas over a slender wing of variable shape

A study is made of the flow of a uniform homogeneous hypersonic ideal gas over the windward side of a slender wing whose surface profile depends on the time; the problem is solved by the thin shock layer method. The bow shock is assumed to be attached to the leading edge of the wing at at least one point. The corrections of the first approximation to the main 'Newtonian' flow are found. For wings of finite aspect ratio, when the bow shock is attached along the whole of the leading edge of the wing, computational formulas are obtained for determining the parameters of the gas in the shock layer.