@article{oai:jaxa.repo.nii.ac.jp:00031352,
 author = {DOI, Takao},
 journal = {The Institute of Space and Astronautical Science report},
 month = {Nov},
 note = {A computational method to solve the gas-particle flows in axisymmetric nozzles is presented for the prediction of the specific impulse of solid propellant motors. In subsonic-transonic region, the particle phase properties are obtained by numerical integration of the characteristic equations along the particle stream lines, and the method of characteristics is then successfully applied to the supersonic region. The effects of the nozzle size, the throat geometry and the propellants on the thrust performance have been investigated in detail. The comparison between the calculation results and the experimental data shows that the specific impulse of practical motors can be well predicted by specifing the effective particle diameter of 1.8μ. The optimum nozzle shapes have been also investigated assuming parabolic contours, and a useful design chart for solid propellant motor nozzles is presented., 資料番号: SA0034896000},
 pages = {1--21},
 title = {Gas-Particle Nozzle Flows and Optimum Nozzle Shape},
 volume = {596},
 year = {1981}
}