An exact solution of a simplified two-phase plume modelAn exact solution of a simplified two-phase, gas-particle, rocket exhaust plume model is presented. It may be used to make the upper-bound estimation of the heat flux and pressure loads due to particle impingement on the objects existing in the rocket exhaust plume. By including the correction factors to be determined experimentally, the present technique will provide realistic data concerning the heat and aerodynamic loads on these objects for design purposes. Excellent agreement in trend between the best available computer solution and the present exact solution is shown.
Document ID
19740060437
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Wang, S.-Y. (Mississippi, University University, Miss., United States)
Roberts, B. B. (NASA Johnson Space Center Houston, Tex., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Subject Category
Thermodynamics And Combustion
Meeting Information
Meeting: Southeastern Conference on Theoretical and Applied Mechanics