AERADE Home
→
Aeronautical Research Council
→
Aeronautical Research Council (1945-1979)
→
Aeronautical Research Council Reports & Memoranda
→
Browsing Aeronautical Research Council Reports & Memoranda by Title

Browsing Aeronautical Research Council Reports & Memoranda by Title

Now showing items 1-20 of 1313

10-ft x 7-ft tunnel tests up to M = 0.94 of nose droop and a blunt-nosed NACA 3-00 type section on a 7.5 per cent thick 50 deg swept wing

A. L. Courtney (1958)

This note describes further tests made during 1954 in the Royal Aircraft Establishment 10 ft x 7 ft High Speed Tunnel, as part of a research programme to improve the subsonic longitudinal stability characteristics of a 50 ...
24-ft tunnel tests on a high-lift model downwash and velocity measurements at the tailplane

C. H. Naylor (1942)

Pitching moment measurements in the 24 ft. tunnel have shown that the highlift model with double Fowler flaps down and slat open, although reasonably stable without slipstream, becomes unstable at the higher thrust ...
24-ft wind tunnel tests on a propeller with NACA 16 series sections. Test results and analysis into mean lift-drag data

A. R. C. MacDougall; A. B. Haines (1948)

This report gives the results of tests made in the Royal Aircraft Establishment 24-ft Wind Tunnel on the de Havilland propeller for the Aeronautical Research Council research programme initiated in 1943. The propeller was ...
24-ft. tunnel tests on a Rotol wooden Spitfire propeller. Test results, and data for single radius calculations

A. B. Haines; P. B. Chater (1946)

This note contains the results of tests made in the Royal Aircraft Establishment 24-ft. tunnel on the Rotol hydulignum propeller RA.10046 designed for the Spitfire IX aircraft. The overall thrust and torque measurements ...
A 2D partially-parabolic procedure for axial-flow turbomachinery cascades

A. K. Singhal; D. Brian Spalding (1976)

A general finite-difference procedure is presented for the calculation of steady, two-dimensional 'partially-parabolic' flows, with special reference to turbine cascade problems. It can be used for incompressible, subsonic, ...
The 9 x 3 in. induced-flow high-speed wind tunnel at the national physical laboratory

D. W. Holder; R. J. North (1949)

A 9 X 3 in. high-speed wind tunnel driven by a compressed-air injector has been built in the Aerodynamics Division of the National Physical Laboratory. The tunnel operates at roughly atmospheric stagnation pressure and has ...
A.R.C. heat and mass transfer sub-committee proposed nomenclature for film cooling investigations

J. Odgers; B. R. Smith (1967)

Under review
Abstracts of papers published externally

Unknown author (1951)

CONTENTS. Repeated Loading and Fatigue Tests on a D.H.104 (Dove) Wing and Fin. Shock-wave and Boundaiy-layer Phenomena near a Flat Surface. Jet Flow and its Effects on Aircraft. A Shielded Hot-wire Anemometer for Low Speeds. ...
Abstracts of Papers Published Externally

[Unknown] (1954)

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.
Abstracts of papers published externally

Unknown author (1949)

CONTENTS: Spring Tabs on Frise Ailerons. Why Shear Webs? A Boundary Value Problem for a Hyperbolic Differential Equation Arising in the Theory of the Non-uniform Supersonic Motion of an Aerofoil. A Study by a Double-refraction ...
Abstracts of papers published externally

Unknown author (1960)

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. ...
The accuracy of the measurement of turbulent skin friction by means of surface pitot-tubes and the distribution of skin friction on a flat plate

R. A. Dutton (1956)

An experimental study has been made of two-dimensional turbulent boundary-layer flow with zero pressure gradient. The investigation was made to determine the accuracy of a method proposed by Preston for measuring the local ...
Accurate solutions of the laminar-boundary-layer equations, for flows having a stagnation point and separation

N. Curle (1958)

An accurate method of solution is developed for steady incompressible laminar boundary layers whose main-stream velocity U(x) is expressible as an odd polynomial in distance x measured along the wall. The velocity distribution ...
Aerodynamic Characteristics in the Approach, Superfine and Negative Pitch Ranges of Two Four-Bladed Propellers with N.A.C.A. Series 16 Blade Sections.

Technical Staffs of de Havilland Propellers; Limited; Rotol; Limited. (1957)

Tests were conducted on two similar full-scale propellers in tim 24-ft Wind Tunnel at the Royal Aircraft Establishment by representatives of Rotol, Ltd. and de Havilland Propellers, Ltd. to measure the aerodynamic ...
The aerodynamic characteristics of flaps

A. D. Young (1947)

This report collects and summarises the results of work that has been done both in this and other countries on the aerodynamic characteristics of flaps prior to and during the period of the war. The report has both a ...
Aerodynamic characteristics of rectangular wings of small aspect ratio

I. J. Campbell; C. F. Blanks; D. A. Leaver (1956)

The results of a programme of low-speed wind-tunnel measurements of the lift, drag and pitching moment on a number of model wings, each fitted with a full-span plain flap, and of a much more limited programme of hinge-moment ...
Aerodynamic coefficients for an oscillating delta wing

Doris E. Lehrian (1951)

Under review
Aerodynamic Data for Three Supercritical Aerofoils, RAE(NPL)9515 AND 9530, AND RAE 9550. Parts I and II

J. L. Fulker (1975)

Part I compares the experimentally determined aerodynamic characteristics of two 10½% thick supercritical aerofoil sections, RAE(NPL)9515 and 9530, over the Mach number range 0.3 to 0.88 and angles of incidence from -0.82° ...
Aerodynamic derivative measurements on a rectangular wing of aspect ratio 3.3

P. R. Guyett; J. K. Curran (1958)

A complete set of oscillatory aerodynamic stiffness and damping derivatives has been determined for a rectangular wing for rigid-wing modes of normal translation, pitch, and roll, in the range of frequency parameter 0.4 ...
Aerodynamic derivative measurements on a wing with a horn-balanced control surface

P. R. Guyett; J. K. Curran (1961)

Some oscillatory aerodynamic derivatives for wing pitch and translation, and control-surface rotation have been found from measurements in a low-speed wind tunnel. The wing was a modified cropped delta of biconvex circular-arc ...

Browsing Aeronautical Research Council Reports & Memoranda by Title

Browsing Aeronautical Research Council Reports & Memoranda by Title

Search AERADE

Browse

All of AERADE

This Collection

My Account