MEASUREMENTS AND CORRELATION OF HEAT TRANSFER IN A SOLID PROPELLANT ROCKET NOZZLE
NAVAL ORDNANCE LAB WHITE OAK MD
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The two-dimensional transient heat flow in a conical De Laval nozzle subject to a solid propellent exhaust flow was investigated. Local temperature and heat transfer rates at the internal surface were determined. It was found that an analysis assuming one-dimensional heat flow gave essentially the same results as the twodimensional analysis. Local heat transfer coefficients were compared with the predictions from a detailed solution of the turbulent boundary layer flow and with the widely used empirical relation of Bartz. The present results were in better agreement with the boundary layer solution, particularly in the prediction of the peak value at the nozzle throat. The present rocket nozzle data expressed in Nusselt number form showed very good agreement with the steady state heat transfer data observed with a water-cooled copper nozzle. On the basis of the present data plus the copper nozzle data a simple adjustment is derived to include the effects of compressibility and geometry in the conventional Nusselt-Reynolds number correlation. This adjustment decreases the scatter of experimental data by 43 percent.
- Solid Propellant Rocket Engines