'Heat transfer at low temperature in the entry section of a solid propellant rocket nozzle'

Smith, A. G.

dc.contributor.author	Smith, A. G.
dc.date.accessioned	2017-06-21T13:37:45Z
dc.date.available	2017-06-21T13:37:45Z
dc.date.issued	1962-04
dc.identifier.uri	http://dspace.lib.cranfield.ac.uk/handle/1826/12082
dc.description.abstract	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.].	en_UK
dc.language.iso	en	en_UK
dc.publisher	College of Aeronautics	en_UK
dc.relation.ispartofseries	CoA/N-125	en_UK
dc.relation.ispartofseries	125	en_UK
dc.title	'Heat transfer at low temperature in the entry section of a solid propellant rocket nozzle'	en_UK
dc.type	Report	en_UK