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 ...
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 is concerned with the design of annular supersonic nozzles to produce uniform flow in supersonic wind tunnels which are axi-symmetrical and which have an internal coaxial circular cylinder throughout. Symmetrical ...
Photo-elastic methods are used to establish how much of a cylindrical steel strut mounted for measurement of compressive force by strain-gauges, has uniform stress distribution, even when the end load is concentrated near ...
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 ...
A subsonic compressor designea to operate at high Mach numbers was tested, the measured pressure ratio being 1.38 at 22 lb/sec/sq ft flow and about 89 per cent efficiency. This efficiency was maintained at 5 per cent ...
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 ...
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 ...
Minimum values of the zero-lift wave drag of slender wings with certain fixed properties have been calculated by slender-body theory. The cross-sectional area distributions of the wings are taken to be polynomials and the ...
Part 1. A simple method of calculating downwash interference is presented and comparison of theoretical and flight test trim curves indicates that the method is reasonably accurate. Since the stability of the tandem-rotor ...
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 ...
A three-stage turbine designed for high stage loading has been tested cold over a wide range of operating conditions and the test results have been compared with calculated performance figures. Inter-blade row traverses ...
The development of special smooth wing constructions for laminar-flow aerofoils calls for a simple testing technique to check the suitability of these new designs. In the method now used a short parallel length of wing ...
Formulae for calculating the-gradients and ordinates of the camber surfaces of swept-back wings of arbitrary plan-form with subsonic leading edges, and specified load distribution, are given, including those which have ...
The object of this investigation was the design of a supersonic wind tunnel for use in determining the internal flow in engine intakes between Mach 1.5 and Mach 3 and in ranges of pitch (+ 15 deg) and engine mass flow ...
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 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 ...
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 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 ...