Navier-Stokes Computations of Base Bleed Projectiles

1988 ◽  
Vol 1 (1-6) ◽  
pp. 93-105
Author(s):  
J. Sahu ◽  
Charles J. Nietubicz
Keyword(s):  
Navier Stokes ◽  
Base Bleed

scholarly journals Optimization of artillery projectiles base drag reduction using hot base flow

2019 ◽  
Vol 23 (1) ◽  
pp. 353-364
Author(s):  
Mohammed Dali ◽  
Slobodan Jaramaz
Keyword(s):  
Drag Reduction ◽  
Stokes Equations ◽  
Flow Characteristics ◽  
Turbulence Models ◽  
Combustion Products ◽  
Base Flow ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Base Bleed ◽  
Base Drag

The CFD numerical simulations were carried out to investigate the base drag characteristics of a projectile with base bleed unit with a central jet. Different base bleed grain types with different combustion temperatures were used. The goal was to find a way to effectively control the base flow for base drag reduction and optimisate the latter using an adequate CFD software. Axisymmetric, compressible, mass-averaged Navier-Stokes equations are solved using the k-? SST, transition k-kl-?, and RSM turbulence models. The various base flow characteristics are obtained by the change in the non-dimensionalized injection impulse. The results obtained through the present study show that there is an optimum bleed condition for all base bleed grains tested. That optimum is dependent on the temperature of the grain combustion products. The optimum reduces the total drag for 6,9% in the case of air injection at temperature of 300 K and reaches up to 28% in the case of propellant combustion products injection at almost 2500 K. Besides, the increasing of molecular weight has a role no less important than temperature of the combustion products in terms of base drag reduction.

Navier-Stokes computations for a reacting, M864 base bleed projectile

1993 ◽  
Author(s):  
CHARLES NIETUBICZ ◽  
HOWARD GIBELING
Keyword(s):  
Navier Stokes ◽  
Base Bleed

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Numerical Results ◽  
Single Stage ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Operating Stability ◽  
Length Coverage

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.

Experimental and Numerical Analysis of a Motorcycle Air Intake System Aerodynamics and Performance

2020 ◽  
Vol 17 (1) ◽  
Author(s):  
M. A. Abd Halim ◽  
N. A. R. Nik Mohd ◽  
M. N. Mohd Nasir ◽  
M. N. Dahalan
Keyword(s):  
Combustion Process ◽  
Three Dimensional ◽  
Engine Performance ◽  
Internal Flow ◽  
Rapid Expansion ◽  
Navier Stokes ◽  
Turbulent Fluctuation ◽  
Ansys Fluent ◽  
Induction System ◽  
Acceleration And Deceleration

Induction system or also known as the breathing system is a sub-component of the internal combustion system that supplies clean air for the combustion process. A good design of the induction system would be able to supply the air with adequate pressure, temperature and density for the combustion process to optimizing the engine performance. The induction system has an internal flow problem with a geometry that has rapid expansion or diverging and converging sections that may lead to sudden acceleration and deceleration of flow, flow separation and cause excessive turbulent fluctuation in the system. The aerodynamic performance of these induction systems influences the pressure drop effect and thus the engine performance. Therefore, in this work, the aerodynamics of motorcycle induction systems is to be investigated for a range of Cubic Feet per Minute (CFM). A three-dimensional simulation of the flow inside a generic 4-stroke motorcycle airbox were done using Reynolds-Averaged Navier Stokes (RANS) Computational Fluid Dynamics (CFD) solver in ANSYS Fluent version 11. The simulation results are validated by an experimental study performed using a flow bench. The study shows that the difference of the validation is 1.54% in average at the total pressure outlet. A potential improvement to the system have been observed and can be done to suit motorsports applications.

Testing of Parts and Complete Units of the Swedish Base Bleed System

1988 ◽  
Vol 1 (1-6) ◽  
pp. 251-270
Author(s):  
Nils-Erik Gunners ◽  
Kurt Andersson ◽  
Yngve Nilsson
Keyword(s):  
Base Bleed

Ignition and Combustion Behavior of MTV Igniter Materials for Base Bleed Applications

1988 ◽  
Vol 1 (1-6) ◽  
pp. 43-61 ◽  
Author(s):  
B. L. Fetherolf ◽  
D. M. Chen ◽  
T. S. Snyder ◽  
T. A. Litzinger ◽  
Kenneth K. Kuo
Keyword(s):  
Combustion Behavior ◽  
Base Bleed ◽  
Ignition And Combustion
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