Exploitation of Multiple Solutions of the Navier-Stokes Equations to Achieve Radically Improved Flight

1989 ◽  
Author(s):  
David Nixon ◽  
S. C. Caruso ◽  
M. Farshchi
Author(s):  
S R Kendall ◽  
H V Rao

Computational models for fluid flow based on the Navier-Stokes equations for compressible fluids led to numerical procedures requiring the solution of simultaneous non-linear algebraic equations. These give rise to the possibility of multiple solutions, and hence there is a need to monitor convergence towards a physically meaningful flow field. The number of possible solutions that may arise is examined, and a mid-cell back substitution technique (MCBST) is developed to detect and avoid convergence towards apparently spurious solutions. The MCBST was used successfully for flow modelling in micron-sized flow passages, and was found to be particularly useful in the early stages of computation, optimizing the speed of convergence.


2019 ◽  
Vol 13 (1) ◽  
pp. 199-219
Author(s):  
Silje K. Almeland ◽  
Nils R. B. Olsen ◽  
Kari Bråveit ◽  
Pravin R. Aryal

AIAA Journal ◽  
2014 ◽  
Vol 52 (8) ◽  
pp. 1686-1698 ◽  
Author(s):  
Dmitry S. Kamenetskiy ◽  
John E. Bussoletti ◽  
Craig L. Hilmes ◽  
Venkat Venkatakrishnan ◽  
Laurence B. Wigton ◽  
...  

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.


AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 56-63
Author(s):  
W. Kyle Anderson ◽  
James C. Newman ◽  
David L. Whitfield ◽  
Eric J. Nielsen

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