Abstract:
An extension of slender-wing theory, introduced by Adams and Sears, has been applied to some problems concerned with the properties of slender, lifting, wings with curved leading edges at supersonic speeds. Two particular problems are considered. These are the calculation of the change in lift, aerodynamic centre, and load distribution on uncambered wings as the Mach number increases above M = 1.0 and the calculation of the camber shape to produce a given load distribution at a given Mach number. Where possible the results are compared with linear theory and with experimental results, and the limitations of the extension are discussed.
