NASA NTRS · 19720000747
Final report on a study of low-density nozzle flows, with application to microthrust rockets
Abstract
Method for predicting nozzle performance of microthrust rockets is discussed. Method is numerical and uses simplified computer program on IBM 360/65 computer. Analysis is based on slender channel equations with slip boundary conditions at walls. Implicit finite difference scheme is used to calculate pressure and velocity profiles along channel.
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1972-12-01. Final report on a study of low-density nozzle flows, with application to microthrust rockets. https://ntrs.nasa.gov/citations/19720000747
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