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Browsing Aeronautical Research Council Reports & Memoranda by Author

Browsing Aeronautical Research Council Reports & Memoranda by Author "E. W. E. Rogers"

Now showing items 1-11 of 11

An experimental investigation of the interaction between a forward-facing step and a laminar boundary layer in supersonic, low-density flow

E. W. E. Rogers; C. J. Berry; B. M. Davis (1965)

The present research programme of the National Physical Laboratory is concerned with the influence exerted on model forces and surface pressures by the thick, laminar boundary layers characteristic of rarefied, near-continuum ...
Experiments at M = 1.41 on a thin, conically-cambered elliptic cone of 30 degrees semi-vertex angle

E. W. E. Rogers; V. G. Quincey; J. Callinan (1961)

Pressure-plotting and strain-gauge balance tests have been made at a Mach number of 1.41 on a conically cambered cone of 30° semi-vertex angle, and with a ratio of the major to the minor axis of its cross-section equal to ...
Experiments at M = 1.41 on elliptic cones with supersonic leading edges

E. W. E. Rogers; C. J. Berry (1955)

Tests have been made at a Mach number of 1.41 on six elliptic cones forming two families of models. In the first, the vertex angle in the plane of the major axes of the elliptic cross-sections was maintained constant at ...
Experiments at M0 = 4.03 on two families of pressure-plotting wing-and-half-cone combinations

E. W. E. Rogers; J. L. Attridge; Miss A. G. J. Macdonald; J. Callinan (1964)

Tests have been made at a Mach number of 4.03 and Reynolds number of 3.4 million on two families of models, consisting of delta wings with underslung half-Cone bodies. The wing sweepback angles were 75° and 80°, and the ...
Experiments with biconvex and double-wedge aerofoils in low-density, supersonic flow

E. W. E. Rogers; C. J. Berry (1968)

This report contains an analysis of the surface-pressuie distributions on two aerofoil sections of 10% thickness/chord ratio, at Math numbers near 2 and 4, and at Reynolds numbers between 93 and 1920, based on model chord. ...
Experiments with cones in low-density flows at mach numbers near 2

E. W. E. Rogers; C. J. Berry; B. M. Davis (1964)

Summary. Tests have been made on the N.P.L. low-density tunnel on two pressure-plotting cones of 15 deg and 30 deg semi-vertex angle placed at zero incidence to the flow. The stream static pressure was varied between 20 ...
An investigation of the flow about a plane half-wing of cropped-delta planform and 6 per cent symmetrical section at stream mach numbers between 0.8 and 1.41

E. W. E. Rogers; I. M. Hall; C. J. Berry (1960)

Summary. A study has been made of the flow development over the wing as the incidence and stream Mach number vary and this is illustrated by surface pressure distributions and oil-flow patterns. The growth and movement of ...
Part I The Flow Pattern on a Tapered Sweptback Wing at Math Numbers between 0.6 and 1.6 Part II Experiments with a Tapered Sweptback Wing of Warren I 2 Planform at Mach Numbers between 0.6 and 1.6

I. M. Hall; E. W. E. Rogers (1960)

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 ...
A study of the effect of leading-edge modifications on the flow over a 50-deg sweptback wing at transonic speeds

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 at high subsonic speeds on a 10 per cent thick pressure-plotting aerofoil of RAE 104 section

E. W. E. Rogers; C. J. Berry; R. F. Cash (1951)

1. Summary and Introduction.--A series of tests has been made in the National Physical Laboratory 20-in. x 8-in. High Speed Wind Tunnel on a two-dimensional pressure-plotting aerofoil of five inches chord and RAE 104 ...
Tests at transonic speeds on wings with wedge sections and sweep varying between 0 degree and 60 degrees

E. W. E. Rogers; C. J. Berry; V. G. Quincey (1961)

Tests have been made in the N.P.L. 18 in. by 14 in. High-Speed Tunnel at stream Mach numbers between 0.6 and 1.2 on two finite wings of identical planform and having single-wedge and double-wedge sections of 14% and 7% ...

Browsing Aeronautical Research Council Reports & Memoranda by Author "E. W. E. Rogers"

Browsing Aeronautical Research Council Reports & Memoranda by Author "E. W. E. Rogers"

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