Summary.--The general method of Pohlhausen, which is discussed in detail in Ref. 1, uses a uniparametric system of velocity distributions of the form u/U = f(y/delta) + lamda.g(y/delta). Pohlhausen, by choosing simple forms ...
Measurements of lift, drag and pitching moment have been made on a series of cropped delta wings of aspect ratio 1.4, 1.2, 1.0 and 0.8 formed by successively cropping a delta-wing model of aspect ratio 1.6. These tests ...
A calculation method has been developed which uses the compressible forms of the boundary-layer momentum integral and entrainment equations in a general, curvilinear surface coordinate system in which the axes are not ...
Some leaded windows have been subjected to a series of sonic bang response tests using a specially developed explosive simulated bang. The tests covered a range of bang pressures and durations. Results show that the ...
Results are presented of a study of the pressures on the flat windward surfaces of two wings with curved, sharp leading edges. The leading edges of one of the wings are convex outwards, whereas those of the second are ...
The steady laminar incompressible boundary-layer problem in two dimensions has been posed as an integral equation in Crocco variables in the most general case and an algorithm developed for computing the similarity flows ...
A detailed comparison of resu[ts has been made from several series of flight tests, spanning a number of years, on the Fairey Delta 2, with wind tunnel tests on 1/9 and 1/24 scale models and with reference also to simple ...
At St. David's Cathedral, structural vibrations produced by a number of Concorde sonic bangs have been measured and compared with the vibration produced by the structures normal environment. The results show that bang ...
An approximate theoretical formula for the distribution of aerodynamic load over arbitrary thick wings in incompressible flow is developed by combining three-dimensional results from thin-wing theory with twodimensional ...
In this report, the Kron eigenvalue procedure is established by the application of Hamilton's principle to a constrained primitive Lagrangian, comprising the characteristics of the various sub-systems into which a composite ...
Compact devices attached to structures for the remote measurement of displacement and strain, utilising pneumatic principles, have potential advantage in long term creep-fatigue conditions, or at very elevated temperature. ...
The following investigation formed part of a more general research on problems associated with high-lift flaps. To obtain the maximum advantage from such devices, a satisfactory alternative to the conventional aileron is ...
A new form of short duration wind tunnel is described in which the test gas is heated employing isentropic compression by a free piston moving in a tube. The piston is propelled by gas from a high pressure reservoir and ...
Some of the more important practical implications to pilot's control, flight test analysis, and stability augmentor performance of classical longitudinal stability theory are discussed. The distinction between turns and ...
Optimal landing transition manoeuvres are studied for jet-lift VTOL aircraft in which the range of engine-tilt is sufficient to allow approach angles up to 20 degrees. The optimal use of incidence, thrust vector angle and ...
The net thrust or drag of a power-plant cooling system has been estimated for various flight speeds. The effect of using the exhaust heat inside the duct is considered, and also the effect of burning additional fuel behind ...
The practicability of allowing approximately for the higher-frequency normal modes of a structure by using a residual flexibility matrix is examined somewhat philosophically. There appears to be a better method of ...
Results are presented for the aerodynamic characteristics of NACA 0012 aerofoil section at Reynolds numbers of 2.88 x 10power6 and 1.44 x 10power6 with some indications of scale effect at other Reynolds numbers. The ...
Some comprehensive calculations of the flow conditions resulting from the intersection of a weak shock wave with a strong shock are presented and discussed, for a range of upstream Mach numbers between 1.4 and 2.8. Such ...
This Report gives a detailed account of the development of a machine for reproducing aircraft motions on a flight simulator cockpit. The four freedoms of the machine are actuated by hydraulic servos. The equipment is part ...