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 ...
A camera has been developed which enables oscillations of shock-waves and of other quasi-stationary phenomena in a wind tunnel to be photographed by either the schlieren method or the shadowgraph method at speeds up to ...
The first part of this report describes the Ngh-speed tunnel installation in the Aerodynamics Division of the National Physical Laboratory. The installation consists of the 12-in. diameter High-Speed Tunnel, the 20 x 8-in. ...
Pressure plotting tests were made in the Royal Aircraft Establishment High Speed Tunnel on a parallel wooden NACA 0015 wing with dive-recovery flap. The Mach number was varied between 0.30 and 0.80, and the Reynolds number ...
Part I - Tests on the Spitfire I. Part II - Tests on the Spiteful (F. 1/43). Part III - Tests on Cabins for the Spiteful. Part IV - Tests on the Attacker (E. 10/44). Part V - Tests on the Mustang I. This report describes ...
Tests have been made in the Royal Aircraft Establishment High-Speed Wind Tunnel on six wings, all of the same plan form (aspect ratio 3.5, taper ratio 0.4, quarter-chord sweep 40 deg) and thickness/chord ratio (10 per cent) ...
The semi-empirical 'equivalent profile' method of W. P. Jones (1948) is extended to the case of an aerofoil with an oscillating control. The oscillatory hinge-moment derivatives for such an aerofoil-control combination in ...