Skin temperatures and heat transfer over wedge wings at extreme speeds of flight

By paying spacial attention to the wing design and altitude of flight, it is possible to ensure that the highest temperature reached at the leading edge of the wing of an aircraft, in level flight at speeds of the order of the circling velocity, need be no more than about 1000*c

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

A numerical method is described for the solution of certain differential equations which result from the application of Crocco’s transformation to the laminar boundary layer equations appropriate to high supersonic Mach numbers. (i.e. at hypersonic speeds). Continues

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

This note comments on the comparison between the answer obtained by linear theory for the wave drag of slender-wings (as interpreted by the limit and that value for the drag obtained by Slender-Body Theory. It is shown that for fully tapered wings the agreement is exact, and that there is reason to suppose that the same is true for all wing planforms, unless the trailing-edge is unswept, or the wing section has a finite trailing-edge thickness. Some remarks are included concerning the drag of slender delta wings

A resume of maximum lift data for symmetrical wings, with various high-lift aids

We shall attempt here to summarise the existing data on the values of the low-speed CLmax of wings, in the absence of a fuselage, and without including information on stalling incidence or pitching moment. The summary is limited to the consideration of unswept wings, and those of delta planforms, which have symmetrical sections: there is some discussion of the maximum lift increments due to the use of flaps of various kinds

Falkner-Skan Flow Over a Wedge with Slip Boundary Conditions

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76718/1/AIAA-2009-476-210.pd

The air resistance of racing cyclists

Tests in the closed-section wind-tunnel on three different cyclists mounted on a racing bicycle are described, and figures quoted for the recorded air resistance. Some comments are also included on the implications of the results concerning the power-output of racing cyclists

Surface conduction of the heat transferred from a boundary layer

This note considers the effect of thermal conductivity upon the temperature distribution in the skin of a body (moving through 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 skin conductivity and thickness, may be appreciably less than the thermometer temperature, particularly at high speeds and altitudes of flight

The two-dimensional laminar boundary layer at hypersonic speeds

A numerical solution is found for the equations governing the motion of a two-dimensional laminar boundary layer, in the absence of a pressure gradient, which would be valid if the flight Mach number is very high (i.e. M2>>1). The effects of surface slip, and the finite thickness of the boundary layer are shown to be negligible if the Reynolds Number (R) exceeds about 105, and are neglected. Continues

A method for numerical evaluation of the integral...

This report presents formulae and data for the numerical evaluation of the double integral named in the title..

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

An expression is deduced for the wave drag of a fully tapered swept wing of arbitrary section in the convenient form of a double integral involving the variation of wing-surface slope. It is concluded, in the general case, that the drag may best be computed by numerical integration, the method for which will be the subject of a further report. Continues