Thermodynamics of Similar ParticleLaden Gas Flows in ConvergentDivergent Nozzles
Abstract
In integral solidpropellant rocket ramjets, a highly fuelrich solidpropellant rocket is imbedded or attached to a supersonic combustion ramjet system to act as a fuelrich hotgas generator. In connection with the consideration of such ramjets, Thomas (1980) and Billig et al. (1980) have discussed gasparticle flows with high loading ratios. The analysis of such flows becomes particularly simple if a steady, onedimensional, similar flow is considered under certain additional assumptions. In the present investigation, the assumption of a constant collisional relaxation time, in addition to the assumption of similarity of flow, makes it possible to demonstrate that the gas and particle velocities increase proportional to the axial coordinate x, the temperatures decrease proportional to the square of x, and the gas state changes with a polytropic exponent n which is constant along the flow and can be calculated.
 Publication:

Journal of Spacecraft and Rockets
 Pub Date:
 July 1982
 DOI:
 10.2514/3.62269
 Bibcode:
 1982JSpRo..19..376B
 Keywords:

 ConvergentDivergent Nozzles;
 Nozzle Flow;
 Solid Propellant Rocket Engines;
 Supersonic Combustion Ramjet Engines;
 Thermodynamic Properties;
 Two Phase Flow;
 Flow Velocity;
 Gas Flow;
 One Dimensional Flow;
 Steady Flow;
 Thermal Expansion;
 Fluid Mechanics and Heat Transfer