An analytical study has been made of the effect of such parameters as wing loading, aspect ratio, thrust-weight ratio, and number of engines, on the takeoff performance of fixed wing aircraft. Expressions are derived for ...
The symmetric response of a tri-jet transport aircraft to continuous atmospheric turbulence and to discrete ramp gusts has been calculated and compared with the results of flight measurements. The aircraft was represented ...
This report briefly describes salient results obtained during commissioning Or the stagnation pressure control system of the N.P.L. 15 in x 10 in (38.1 cm x 25.4 cm) blowdown wind tunnel. The very different problems of low ...
An algebraic solution is given for the problem of ascertaining the probability of finding any number of fatigue cracks in a fleet of aircraft at any specific point in time. By a simple approximation concerning the fatigue ...
As an aid to discussions on the future provision of meteorological forecasting services for civil transport operations, an approximate assessment is made of the effects of changes in the accuracy with which en-route and ...
Part span sharpened leading-edges were attached to the wing to produce regions of separated flow. Flight measurements were made of both the spectra and root-mean-square intensity of the pressure fluctuations at orifices ...
The stability of aircrew breathing equipment depends not only on the stability of the oxygen regulator, but also on the impedance of the system it feeds, which includes the user's respiratory system. A method of measuring ...
C. W. Skingle; N. M. Willcox; D. R. Gaukroger(1968)
The spectra of pressures at points in and behind the bomb bay of a Canberra aircraft have been obtained for a range of flight conditions. The primary objective of the flight measurement programme was to acquire data for ...
Mean pressure recovery, distortion and the extent of stable subcritical flow have been measured at zero incidence on a fuselage side intake having a wedge compression surface. The intake was separated from the fuselage by ...
A thick-walled tube was subjected to an axial load and a radial temperature distribution which caused thermal stresses. The creep strains and the eventual rupture times were observed and compared with conventional creep ...
Calculations are presented of the compressible turbulent boundary layer on a flat plate. They have been made by a new, general, accurate and economical procedure. The physical inputs chiefly comprise: (1) a form of the ...
A series of experiments have been performed with a rotating cascade wind tunnel to determine the effect of a rotational flow on the behaviour of the blades in a turbomachine. A two-bladed rotor has been tested as a stationary ...
The paper sets out to summarise the properties of the flow in a local supersonic, two-dimensional, steady potential flow region. Starting from the results of the theory of characteristics, the concept of wave strength is ...
An analysis is given of the relationship between power spectra of image density variations in a schlieren film of a hypersonic wake and the power spectra of gas density variations in the wake. Some results are given for ...
There are many good reasons for attempting to predict creep behaviour under conditions of varying stress and temperature from data derived from tests perfomed at constant stress and temperature. This Report starts by ...
L. Davies; K. Dolman; D. R. Brown; G. Hooper(1968)
The driver-reservoir technique, first proposed by Henshall et al, is of interest to shock tunnel users because of its promise of an increase in running time. The most usual form of termination of running time in the shock ...
Measurements have been made of vortex breakdown position on a series of symmetrical delta wings of 70 degrees sweep angle but differing thickness distribution using a schlieren system to detect the breakdown. The results ...
A method of calculating the fuel boiling losses, due to aerodynamic heating, from a supersonic aircraft with integral wing fuel tanks is devised and is applied to the Concord, assuming flight conditions of Mach 2.2 at 64000 ...
Normal force and pitching moment have been measured on a number of cone cylinder combinations at a Mach number of 3.98 in the 3 ft x 4 ft High Supersonic Speed Tunnel. The results are presented graphically. Comparison is ...
Supersonic wind tunnel tests were made over an incidence range from -4 to +30 degrees for a range of roll angles on a scrims of conical slender delta wing and body combinations with a short afterbody on which a rectangular ...