Smith, A. G.
Description:
Heat transfer in the converging section of the nozzle of
a simulated solid propellant rocket with a star-shaped conduit
has been investigated in the following way:
(a) Area-average heat transfer has been measured on a room temperature
rig, with and without a simulated charge.
(b) Theoretical heat transfer has been calculated without
the charge (axisymmetric laminar flow).
(0) An attempt has been made to predict the detailed
distribution of heat transfer by measurements of mass
transfer on a nozzle made of napthalene.
(d) Flow visualisation has been performed on a water-rig … [cont.].