Established turbulent boundary-layer methods for predicting throat heat fluxes are often conservative by factors of two or more when applied to low-thrust rocket engines; wall-temperature data from liquid-rocket tests employing three nozzle contours in 20- to 100-lb thrust, 100- to 3000-psia chamber-pressure range, with various injectors are presented; it is shown that thermal wall conditions can be predicated by means of local convective heat-transfer coefficients, calculated from Colburn flat-plate relation for laminar flow; method of obtaining reference position for length parameter in Reynolds number is suggested; approach provides data correlation in transonic and supersonic flow regions. (07552)
Laminar boundary-layer heat transfer in low-thrust rocket nozzles
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 9
1968
8 pages
Article (Journal)
English
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