Specific impulses and combustion temperatures have been circulated for rocket propellants consisting of liquid oxygen and ethyl alcohol-water mixtures. This system appears to have a number of advantages compared with the ...
The Polygon method of Woods is used to calculate the velocity distribution over a number of two-dimensional aerofoils at low incidence, subcritical flows only being considered. Lift slopes and aerodynamic centres at zero ...
Stability and flutter derivatives are obtained for rectangular wings describing plunging and pitching oscillations in subsonic flow. These are evaluated by applying the simple approximate 'equivalent' wing theory (R. & M. ...
A method for the calculation of three-dimensional turbulent boundary layers is given. It depends on the assumptions that the component of the velocity in the boundary layer parallel to the external streamlines follows a ...
Five methods for the approximate solution of the momentum integral equations for the three dimensional turbulent boundary layer are presented. These include the removal of the usual small cross-flow velocity restriction ...
The object of a blade-to-blade method is to calculate the blade surface velocity distribution and the outlet angle for a given three-dimensional cascade. These give the heat drop or work done and indicate whether shock ...
Calculations are presented of the compressible turbulent boundary layer on a flat plate. They have been made by a new, general, accurate and economical procedure. The physical inputs chiefly comprise: (1) a form of the ...
Summary.--The lift, pitching moment and hinge moment are derived for a delta wing with a trailing-edge flap of constant chord when tile wing is at zero incidence in a supersonic air stream and tile flap oscillates harmonically ...
Summary.--The lift, pitching moment and full-span constant-chord control hinge-moment are derived for a cropped delta wing describing harmonic plunging and pitching oscillations of small amplitude and low-frequency parameter ...
This report describes an application of a digital computer to the aerodynamic design and automatic control of a large wind tunnel with flexible walls. The computational problem was threefold : first, calculation of the ...
The vortex-lattice method of calculating flutter derivatives presented in this note is an extension to higher frequencies of the work on stability derivatives reported in R. & M. 2922. The method is a modified form of the ...
A numerical method of solving the integral equation connecting the lift and downwash on a wing oscillating harmonically in a supersonic flow of any Mach number is described. The integral equation is replaced by a matrix ...