During the preparation at the N.P.L. of a manual of tunnel interference the necessity arose for calculating additional values of the blockage-interference corrections for small bodies in incompressible flow in rectangular ...
It is shown on the basis of the linearised theory that the effects of compressibility on the lift and hinge-moment characteristics of a wing and full-span control are functions of aspect ratio. With reduction in aspect ...
The influence of spanwise flow on the lift distribution for a thin flexible wing of any plan form is considered. By the use of Eulel's equations for incompressible, inviscid flow, it is shown that the lift distribution is ...
In studying anct comparing various theories for the determination of the distribution of loading on wings, Garner has given values for the lift slope of several families of swept-back and delta wings deduced from several ...
The maintenance of laminar-flow wings involves two problems:-- (1) The prevention of deterioration in the surface itself (e.g. cracking of the paint or filler, increase in roughness or waviness, etc., whether due to ...
(a) Purpose of Note.--To draw attention to certain restrictions on the use of the 'Southwell plot' to estimate critical loads in cases differing in conditions from those which the method was first proposed. (b) Range of ...
A re-assessment of a generally accepted theory of parachute stability has been made with the object of clarifying the assumptions used in its derivation and exposing deficiencies in previous treatments. Some new, equations ...
Existing theories for the Stanton tube are critically reviewed, and the paper then outlines a simple method which predicts the calibration function at high Reynolds numbers to the right order of magnitude.
A description is given of the three-dimensional shock-wave recorder which has been used to investigate wind-tunnel interference on a sting-mounted wing having 50 deg of sweepback. Diagrams of the shock-wave patterns round ...
Accessible information about the performance of existing wind tunnels is far from being adequate. Once a tunnel is constructed the subject too often becomes a matter of low priority or else such information as is obtained ...
Calculations have been made of the changes in rotor speed following engine failure on a typical helicopter in hovering flight. Various time functions for the collective pitch operation are considered. The results are in ...
Linear differential equations whose coefficients are functions of the independent variable are now assuming importance in aeronautics in the discussion of the motion following a small disturbance in a specified accelerated ...
The downwash induced by planar vorticity distributions has been computed by exact linear theory and by the R.A.E. Standard Method to examine the accuracy of the approximate method. The results on wings of infinite span ...
The design of two-dimensional converging channels is considered, with special reference to (i) the lengths of the channels and (ii) the occurrence or absence of unfavourable velocity gradients at the walls. It is shown ...
A collection of records showing the time histories of strains and accelerations at various parts of a Lancaster flying in turbulent air is presented and discussed. The records include specimens taken in cloud at moderate ...
An expression has been derived for the factor to he applied to ideal induced drag to allow for Wing-tail interference. This factor is primarily dependant on the wing-taillift and span ratios. It is of the order of 1.1 for ...
The existing data have been analysed and a method has been derived for predicting the lift and profile-drag increments of split and slotted flaps. It is suggested that the probable order of error involved in the method is ...
A summary of the first ten flights made with a heat-transfer vehicle is given together with some of the salient features of the results relative to conical and hemispherical heads. The method of reducing the temperature ...