PART I. Tests were made in the Royal Aircraft Establishment No. 19 (18 in. x 18 in.) supersonic wind tunnel to measure the overall normal and side forces, rolling, pitching and yawing moments on a typical canard aircraft ...
Summary. Wind-tunnel tests have been made at a Mach number of 2.92 to measure the effect of humidity on laminar recovery temperature on a cone. Its effect is to increase the recovery temperature above that obtained with ...
The classical theory of wind-tunnel interference is extended to cover interference on the effectiveness of a full-span jet flap issuing from the trailing edge of a high aspect ratio unswept wing. It is shown that, for small ...
Flow photographs and detailed pressure distributions for a 4 per cent thick circular-arc biconvex aerofoil at transonic speeds are presented. The results for incidences of 0, 1, 2 and 5 deg are analysed in detail.
The equations of attitude motion are derived for small angular displacements from the equilibrium position of an earth-pointing satellite employing reaction-flywheel damping. This is followed by a discussion on the attitude ...
An axially-symmetrical supersonic fully-expanded jet of diameter 0.75 in. was investigated by pitot- and static-tube traverses in the region from the exit to 100 diameters downstream. The investigation is supplementary to ...
Numerical methods are given for calculating the double integral ... for the three cases: (i) F(x) is given numerically, (ii) F(x) is the first derivative of a numerically given function, (iii) F(x) is the second derivative ...
On the assumption that the/tow normal to the external streamlines is small compared with that along the external streamlines it is shown that the streamwise momentum equation, the energy equation and the equation of ...
A recent study of velocity profiles in the turbulent boundary layer on a flat plate at high Mach numbers has suggested the formula for relating the form parameter H to its incompressible value Hi. This formula is used in ...
Three different approximate methods of solving the three-dimensional laminar boundary-layer equations are tested on a problem whose exact solution is known. From the comparison one of the methods, which is developed in ...
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 ...
A theory of the Mach-Zehnder interferometer is developed using the approach of investigating the history of a wave front produced by an element of an extended light source. Account is taken of the effects of imperfections ...
The method developed by C. E. Watkins and J. H. Berman in N.A.C.A. Report 1099 and N.A.C.A. Technical Note 3009 is used to obtain the velocity potential on a triangular (or related) wing with subsonic leading edges oscillating ...
This paper has been prepared for publication from several papers written some years ago. It is essentially a new presentation of the more important features of the earlier papers. The paper is about the transonic area rule, ...
The report describes a theoretical investigation in support of measurements being made on an oscillating half-wing model of the plan-form shown in Fig. 1 in the National Physical Laboratory 25 in. by 20 in. Wind Tunnel ...
This Note contains the results of a survey on aerodynamic derivative measurements since 1940 made in both this country and abroad. References are given to 53 papers on the subject and it is believed that most of the published ...
A study is made of some existing analytical, numerical and experimental results for gas jets expanding out of axi-symmetrical nozzles. Jets expanding into a vacuum and into still air at finite pressure are considered in ...
This Report describes an experimental investigation of the factors affecting the base flow and jet structure behind a cylindrical after-body with a central nozzle. Seven interchangeable nozzles were tested. Six of these ...
Observations made in the viscous sub-layer of turbulent shear flows with small surface pitot-tubes and hot wires show that such instruments give accurate values of boundaryiayer skin friction, at least in zero pressure ...
This Report describes the principles to be used in designing an apparatus, including half-model of an aircraft, for measuring longitudinal oscillatory aerodynamic derivatives in the R.A.E. High Speed Tunnel. The model is ...