This report is a continuation of three earlier ones by the present authors (1947-9) and contains a theoretical investigation of subsonic flow past thin tapered unswept wings (of full or cropped-rhombus plan form), at zero ...
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 ...
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 ...
The report gives particulars of a method of calculation, which has been programmed for a digital computer, for linearized two-dimensional subsonic unsteady flow through a cascade of flat plates operating at zero mean ...
A technique for observing flow in vortex cores in flight is described and the results of flight tests to study vortex breakdown using the HP 115 aircraft are presented.
The vortex drag of a lifting surface depends only on its spanwise loading and is usually calculated therefrom. Deflection of a part-span flap gives a theoretical spanwise loading that can only be obtained by numerical ...
This paper outlines the importance of tip leakage flows in axial fans as a source of loss and relates the dimensionless loss analytically to a range of dimensionless parameters by application of a jet loss theory due to ...
The vortex-lattice method for simple harmonic motion of general frequency (R. & M. 2961) is used to calculate the derivatives for rectangular wings with oscillating constant-chord flaps. The discontinuous chordwise boundary ...