Description:
The study deals mainly with engineering problems associated with
the introduction of a noise generating facility on 'Lincoln' aircraft
R.F.342 for the purpose of studying the effect of high intensity sound
pressure levels at both random and discrete frequencies on the laminar
flow fin currently being tested in this aircraft.
The frequencies selected as representative of both turbulent boundary
layer and propulsion system disturbances lie within the band. 200 to 2000
c.p.s. with an upper limit of 1200 c.p.s. for discrete work. Required
sound pressure level at the fin surface is estimated to be 130 db.
Conclusions are that the project is feasible but with the reservation
that certain estimated figures and effects will require to be confirmed by
a test programme prior to mounting the full-scale experiment.