Numerical Simulation of Cold Swirl Field for Solid Fuel Ramjet with NACA Airfoil

Jie Yu; Xiong Chen; Hong Wen Li

doi:10.4028/www.scientific.net/AMM.716-717.711

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 716-717Numerical Simulation of Cold Swirl Field for Solid...

Numerical Simulation of Cold Swirl Field for Solid Fuel Ramjet with NACA Airfoil

Abstract:

In order to study the swirl flow characteristics in the solid fuel ramjet chamber, a new type of annular vane swirler with NACA airfoil is designed. The cold swirl flow field in the chamber is numerically simulated with different camber and t attack angle, while the swirl number , swirl flow field structure, total pressure recovery coefficient were studied. According to numerical simulation result, the main factors in swirl number are camber and angle of attack, the greater angle of attack, the greater the camber ,the stronger swirl will be. Results show that the total pressure loss is mainly concentrated in the inlet section, the total pressure loss cause by vane swirler is small. Radial velocity gradient exists in swirling flow, and increases with the swirl number. With the influence of centrifugal force and combustion chamber structure, the radial velocity gradient increases.

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Periodical:

Applied Mechanics and Materials (Volumes 716-717)

Pages:

711-716

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.716-717.711

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Online since:

December 2014

Authors:

Jie Yu*, Xiong Chen, Hong Wen Li

Keywords:

Cold Swirl Flow Field, NACA Airfoil, Numerical Simulation, Swirl

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