The aim of this paper is the design of optimum wings for the hypersonic range. In order to simplify the problem various assumptions are made, which however still allows us to obtain results of practical value. The problem is considered in the framework of classical aerodynamics, inviscid perfect gas. This restricts the Mach numbers from being so high that real gas effects are important, although as far as lift and wave drag are concerned they do not play a major part. Conical wings are considered which helps to reduce the number of variables and which are practical shapes. Also the focus is on the pressure distribution on the lower surface of a lifting wing which provides the main component of the lift. Further hypersonic small disturbance theory is used to describe the flow. This theory is very accurate in the appropriate range and helps by giving a similarity law, an analogy to unsteady flow and reducing the number of dependent variables. With all these assumptions the problem of finding an optimum becomes very tractable, although a large number of computations are still required.
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