An experimental study of sonic and supersonic nozzles and their application to high pressure ejectors for aircraft attitude control.
A study has been conducted of reaction controls for VSTOL
aircraft using thrust augmenting ejector techniques.
Rapid mixing nozzles have been developed for high pressure
ejectors. Mass flow increases for sonic nozzles of up to
50\ at x/D=8 were recorded, compared with plain circular
nozzles. Their use was found to improve the thrust
performance of a simple ejector by 9\, and larger increases
are believed possible.
Results from an ejector performance prediction model were
successfully compared with experimental data. The use of
rapid mixing nozzles in a practical ejector design has been
assessed. It is predicted that a maximum thrust increment
of 20\ ·could be achieved, compared with a simple fully
expanded jet flow.