This thesis is concerned with the development of a theory for determining the aerodynamic forces for unsteady, compressible subsonic
flow on a propeller and helicopter rotor. The acceleration potential
method was used in developing the basic equations and the method has
been programmed for the propeller on a computer and some results are
given. The integral equations was solved by the doublet-lattice method,
which consists of placing "load" lines at certain locations on the
chord and satisfying the down-vash condition at other selected positions.
The examples presented include the spanvise and chordwise loading
on a rotating propeller for incompressible flow, an example of compressible
flow calculations and finally, a calculation illustrating the loss
of aerodynamic damping of a propeller blade due to the passage of the
blade over its own wake.
A Doctoral Thesis. Submitted in partial fulfilment of the requirements for the award of Doctor of Philosophy of Loughborough University.