Heat Transfer Studies on a Rocket Nozzle for Naval Application

Abstract

where he performed studies on rocket nozzles and aerodynamic heating for the Navy's missile program. Dr. Glen R. Moore received his B.S. degree in mechanical engineering from Wichita State University in I967 and his M.S. and Ph.D. degrees in mechanical engineering from Arizona State University in 1969 and 1971. Since 1971 he has been employed by the Naval Surface Weapons Center, Dahlgren, Virginia. He has been extensively involved in the analysis and testing of Navy gun and mkile system launch environments and their effects on personnel, equipment, and ships. Dr. Moore has authored numerous reports and papers on gun blast and rocket motor plume environments. He is currently a member of the JANNAF Exhaust Plume Technology Subcommittee. Dr. Charles T. Boyer received his B.S., M.S. and Ph.D. degrees from Virginia Polytechnic Institute and State University in 1969, I971 and 1984. He served as an intelligence officer and battery commander in the U.S. Army from 1971 until 1973 in Germany. Since 1974 he has worked at the Naval Surface Weapons Center, Dahlgren, Virginia. He was involved with the analysis and design of gun propelling charge assemblies and with the analysis and measurement of heat transfer from these charge assemblies to the gun bore from 1974 through 1980.Since 1980, he has analyzed and measured the heat transfer from rocket exhaust plumes to ablators used to protect ships and their equipment. He has also analyzed the in-depth heat transfer in these ablators. Currently, Dr. Boyer is the project manager for the generic booster/vertical launching system compatibility test program. He has authored numerous reports and papers on all of this work. ABSTRACTHeat transfer results are presented here for a rocket nozzle that uses aluminized solid propellant. The Solid Performance Computer Program (SPP) was employed to calculate the twodimensional, two-phase flow properties inside the nozzle. Utilizing the properties of particle phase obtained from this program, calculations were made for the heat flux due to particle impingement. Predictions are also presented for convective and radiative heat transfer along the nozzle surface. A comparison was made to assess the magnitudes of various modes of heat transfer. The methodology and results presented in this paper should provide useful data to designers of new rocket nozzles and should aid studies to improve the design of existing nozzles.