Computational study of the pin nozzle geometry and the flight conditions influence on the thrust characteristics
Published: 14.05.2025
Authors: Taran K.A., Fedotova K.V.
Published in issue: #5(161)/2025
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
The paper provides results of a numerical study of the outflow from the model pointed and shortened pin nozzles at the coflow different gas expansion ratios and Mach numbers. Computation is performed in the 2D axisymmetric stationary formulation, and is based on solution to the Reynolds-averaged Navier—Stokes equations closed by the k—ω SST turbulence model and the ideal gas state equation. The obtained distributions relative to pressure distributions along the pin length are validated against the available experimental data; and they are compared at the different Mach numbers. Analysis of the supercritical thrust coefficient values at the flow 4 Mach numbers shows that with the increasing flight velocity, the thrust coefficient is increasing in the subsonic flow and decreases in the supersonic flow. The paper notes that shortening the pin nozzle ensures a significant advantage in mass with an insignificant loss in thrust.
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