The incompressible laminar boundary layer over a slender body of revolution at small incidence

This work investigated the problem described by the title, by solving the linearised perturbation equations for the incompressible flow within the boundary layer of a body of revolution at incidence, using slender body theory to describe the inviscid flow field. The calculations were made by digital computer, using adaptive procedures to keep...

Four papers contributed by members of the staff and published on the occasion of the 10th anniversary of its foundation

Thermo-elastic formulae for the analysis of beams / W.S. Hemp Some aspects of turbojet performance calculation at high flight mach numbers / J.R. Palmer The possible use of semiconductor devices in aircraft / D.C. Brown Conduction of heat within a structure subjected to kinetic heating / T. Nonweiler The College of Aeronautics was founded in...

The air resistance of racing cyclists

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

Skin temperatures and heat transfer over wedge wings at extreme speeds

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

A method for the numerical evaluation of an integral: Occuring in the expression for the wave drag of slender bodies

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The wave drag of highly-swept wings: A comparison of linear theory and slender body theory

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The theoretical wave drag at zero lift of fully tapered swept wings of arbitrary section

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The numerical solution of certain differential equations occuring in Crocco's theory of the laminar boundary layer

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The two-dimensional laminar boundary layer at hypersonic speeds

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The Laminar Boundary Layer in Slip Flow

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

Surface Conduction of the Heat Transferred from a Boundary Layer

This note considers the effects of thermal conductivity upon the temperature distribution in the skin of a body (moving through the air) due to the heat transferred from the boundary layer. It is found that the effects are of importance only very near the nose of the body, and that here the temperature reaches a maximum which, depending on the...

Theoretical stability derivates of a highly swept delta wing and slender body combination

The stability derivatives of a delta wing of small aspect ratio, mounted on a cylindrical body with a slender pointed head, are derived by considering the flow in planes perpendicular to the body axis to be uninfluenced by the change in the streamwise component of the air velocity (the so-called 'slender body' theory). The results are tabulated,...