E. W. E. Rogers; C. J. Berry; J. E. G. Townsend(1960)
An investigation has been made in the N.P.L. 18 in. x 14 in. Tunnel of the effects of leading-edge modifications on the flow and forces on an untapered wing of 50 deg leading-edge sweep, at stream Mach numbers between 0.60 ...
Tests have been made in the A.R.A. 9 ft x 8 ft Transonic Tunnel on a model having a 6% thick, 55° sweptback wing with a warp distribution designed to give a constant spanwise C m - distribution and a triangular chordwise ...
A simple method of calculating the pressure distribution in incompressible flow on two-dimensional aerofoils of arbitrary section at moderate distances from the ground is developed. Comparisons with an 'exact' potential-flow ...
This paper discusses the basic principles employed in techniques for the measurement of oscillatory derivatives in wind tunnels, and gives some account of the associated instrumentation. The suitability of the various ...
A 36 x 35 in. transonic working section with slotted walls on all four sides is described. It is interchangeable with the original supersonic working section of the 3-ft. tunnel, and is used for tests at Mach numbers up ...
Extensive tables are given of pressure coefficients measured at Reynolds numbers from 1.3 x 10power6 to 3.9 x 10power6 on two half-models of identical planform with 5% RAE 101 and 9% RAE 101 streamwise sections. The planform ...
This Report gives a method for calculating the aerodynamic forces and moments acting on unstalled vibrating cascade blades. The forces and moments due to both bending and torsional vibration are calculated, and also due ...
Measurements of the roll-damping derivative of three wing planforms were made by the free-flight roll-balance technique over the Mach number range 0.7 to 1.4. The wings were all of RAE 102 section, 7.5 per cent t/c and ...
PART I. The development of the flow pattern on a swept wing with incidence and stream Mach number is described. The wing, of aspect ratio 2.828, taper ratio 0.333 and leading-edge sweep 53.5 deg, was tested at Mach numbers ...
Note.--All papers discussed by the Aeronautical Research Council and recommended by them for external publication after 1st April, 1932, have been published in abstract only in the Reports and Memoranda Series. CONTENTS. ...
In special circumstances where a large work output is required from a turbine in a single stage it is necessary to us e high pressure ratios across the nozzle blades, thus producing supersonic velocities at inlet to the ...
The Report describes an analyser which was developed for finding the power spectra of waveforms derived from vibrating axial compressor blades due to random excitation. The bandwidth of the instrument goes down to about ...
A continuous solution is derived for the stress distribution in a simple wing surface represented by a uniformly reinforced stri p bounded by equal constant area edge members, when the sections in the airstream experience ...
Foreword (1961). Parts I and II of this R. & M. were written as separate Reports in 1958 and 1960. They deal with two stages of an exploratory investigation into the stability, control and response characteristics of ...
The relation between the discrete gust and the spectral presentations of atmospheric turbulence is discussed and the limitations of the discrete gust approach are pointed out. The available measurements of low-altitude ...
Summary. This report describes an investigation into the effect of blowing a jet stream, simulating conventional jet engines, downwards from the lower surface of a slender delta wing (aspect ratio unity), for the purpose ...
This Report gives experimental values of Nusselt number as a function of Reynolds number and surface/gas temperature ratio for three gases, air, helium and carbon dioxide, and shows the effects of radial variations of fluid ...
The fundamental problem of structural design is the determination of structures of minimum weight which safely equilibrate a given system of external forces. The classical theorem of Michell gave the basic requirements for ...
Part I. In this Report numerical methods used to solve the Navier-Stokes equations for steady viscous two-dimensional flow are extended to include the case of axial symmetry. The equations and their finite difference ...
Available data on the pressure distribution around a hemisphere at supersonic speeds are reviewed with special reference to the differential pressure. A modified form of pressure coefficient is used which collapses the ...