Hypersonic Laminar Heat Transfer and Boundary Layer Transition on Blunted Cones

Abstract

SummaryMeasurements have been made of laminar and transitional heat transfer rate distribution on a 15° semi-vertex angle, spherically blunted, cone at Mach numbers 8·6, 10·6 and 13·0. The laminar results are compared with theoretical predictions and good agreement is obtained with a modified form of the analysis due to Lees. Using a development of the correlation of pressure distributions previously obtained by the author, a new correlation of experimental and theoretical heat transfer results is suggested. The effect of nose bluntness on boundary layer transition has been observed both from flow visualisation and heat transfer results. It is suggested that the main factor causing nose bluntness to influence transition is the adverse pressure gradient which is induced.

The Effect of Condensation on Hypersonic Laminar Heat Transfer to Cones

“…The thin skin calorimeter technique was used to make the measurements and the model, instrumented with thermocouples, was the same as that described in ref. 3 but with a sharp nose piece in position. Details of the model are summarised in Table II.…”