A straightforward procedure has been developed to quickly determine an inviscid design of a hypersonic wind tunnel nozzle when the test gas is both calorically and thermally imperfect. This real gas procedure divides the nozzle into four distinct parts: subsonic, throat to conical, conical, and turning flow regions. The design process is greatly simplified by treating the imperfect gas effects ...

We establish the existence and stability of multidimensional transonic flows with transonic shocks through an infinite nozzle of arbitrary cross-sections, including a slowly varying de Lavel nozzle. The transonic flow is governed by the inviscid steady potential flow equation with supersonic upstream flow at the entrance, uniform subsonic downstream flow at the infinite exit, and the slip bound...

Fuel after inflaming burns at high (till 15-20 МПа and more) pressure, thus is formed gaseous combustion products with temperature 3000-4500 K, which effuse to the ambient space through the nozzle. On length of the nozzle the temperature and pressure of them decrease, and the velocity increases, passing through a sound velocity in minimum (critical) cross-section of the nozzle and reaching 2700...

A theoretical study analyzing three-dimensional combustion acoustic instabilities in a liquid propellant rocket engine combustor has been conducted. A linear theory based on Crocco’s pressure sensitive time lag model is used. To apply this theory the combustor is divided into two main components, including the combustion chamber and the converging part of the nozzle. The assumption of concentra...

The in-gas-jet laser spectroscopy method relies on the production of uniform and low-temperature gas jets to fully resolve atomic hyperfine structure efficiently determine fundamental nuclear properties short-lived isotopes from, e.g., hardly accessible actinide transactinide elements. In this article we present studies devoted designing, producing, characterizing flow a convergent-divergent (d...