Numerical studies of nozzle thrust characteristics of supersonic civil aircraft by computational gas dynamics method

2019 ◽  
Vol 26 (4) ◽  
pp. 7-16
Author(s):  
Vladlen Gorbovskoi ◽  
Andrey Kazhan ◽  
Vyacheslav Kazhan ◽  
Andre Shenkin
Keyword(s):  
Gas Dynamics ◽  
Computational Gas Dynamics ◽  
Numerical Studies ◽  
Civil Aircraft ◽  
Thrust Characteristics ◽  
Nozzle Thrust ◽  
Dynamics Method

scholarly journals DESAIN NOSEL ROKET CAIR RCX250 MENGGUNAKAN METODE PARABOLIK DENGAN MODIFIKASI SUDUT EKSPANSI

2012 ◽  
Vol 9 (1) ◽  
Author(s):  
Eko Priamadi ◽  
Arif Nur Hakim ◽  
Romie O. Bura
Keyword(s):  
Fluid Dynamics ◽  
Design Method ◽  
Exit Angle ◽  
Nozzle Design ◽  
Conical Nozzle ◽  
Initial Angle ◽  
Simulation Results ◽  
Nozzle Thrust ◽  
Dynamics Method ◽  
Maximum Thrust

 The present research is conducted to design the optimum nozzles for RCX250 engine, that is designed to produce maximum thrust of 250 kgf with combination of LOX and Kerosene as its propellant. The new nozzles were determined to be parabolic nozzle, with conical nozzle as its comparison. The parabolic nozzle was designed using Thrust Optimized Parabolic (TOP) method invented by G.V.R.Rao. TOP nozzle design method is performed by approximating a Thrust Optimized Contoured (TOC) Nozzle using parabolic equation. The method would result more efficient nozzle than conical or ideal bell nozzle. Further, the parabolic nozzle were modified in its initial and exit angle to create uniform velocities distribution at nozzle exit. A Computational Fluid Dynamics Method (CFD) is used to simulate the nozzle designs. The simulation was carried out in axis-symmetric condition using commercial CFD software. The simulation results show that MOD 1 nozzle, with initial angle (θN) 26 deg and exit angle (θe) 12 deg, gives maximum thrust, which is 4.67 % higher than reference conical nozzle. Key words:Liquid rocket, Parabolic nozzle, Thrust, CFD

scholarly journals Сalculated analysis of the influence of operation and design factors on the parameters of oxygen-hydrogen low-thrust rocket engines

2019 ◽  
Vol 18 (3) ◽  
pp. 131-142
Author(s):  
V. V. Ryzhkov ◽  
I. I. Morozov
Keyword(s):  
Combustion Chamber ◽  
Gas Dynamics ◽  
Selection Criterion ◽  
Design Parameters ◽  
Rocket Engines ◽  
Low Thrust ◽  
Gaseous Oxygen ◽  
Computational Gas Dynamics ◽  
Design Factors ◽  
Selection Of

The paper presents the results of calculating thermodynamic and thermophysical properties of the combustion products of gaseous oxygen-hydrogen fuel according to the ideal LRE model taking into account the phase state of the components, as well as the parameters of a low-thrust engine according to the model of computational gas dynamics to ensure the selection of operation and design factors that define the design of a thruster for advanced aerospace objects. It is shown that ideal models can be used for the selection of some parameters, such as: the excess oxidant ratio, the pressure in the combustion chamber, the geometric degree of area expansion ratio. High-level computational gas dynamics models need to be used for the selection of some of the parameters of the engine to be designed, such as: design parameters of the propellant injection pattern, reduced length of the combustion chamber and some others. Air specific impulse was used as the selection criterion. The obtained calculation data allow one to choose the main parameters of the engine being designed with account for real processes in the combustion chamber and the nozzle of the engine.

scholarly journals Controlling Noise and Gas Emissions by a New Design of Diesel Particulate Filters

2020 ◽  
Vol 15 ◽  
Keyword(s):  
Gas Dynamics ◽  
Life Time ◽  
Particulate Filter ◽  
New Materials ◽  
Diesel Particulate ◽  
Diesel Particulate Filters ◽  
Particulate Filters ◽  
Numerical Studies ◽  
Research Goal ◽  
Environmental Emissions

A theoretical and numerical studies on Diesel Particulate Filters (DPF) and its working principal in controlling noise and exhaust gasses emissions is presented here. This research includes a study of current Martials types that is used in diesel particulate nowadays and on a new materials and technologies that we can use in future. A new design of DPF is presented here. Unfortunately, in Jordan we face an environmental problems caused by diesel engines and the production of NOx and other exhaust gases and particulate matter. The main reason of this problem is the low specification of diesel fuel that is used in Jordan, which leads to shorten the life time of the Diesel particulate filters and leading to block them in some intensive cases. This problems leads to increasing the pollutant in the air which can harm the people's health, animal and plants, so this research goal is to find a solution for the diesel particulate filter life time and to control the environmental emissions and engines noise resulted from gas dynamics. It is found that the developed design of DPF achieves about 22% increase in its performance in both gas emission and noise reductions comparing with the traditional one.

Lagrangian visualization methods in computational gas dynamics

2019 ◽  
pp. 13-22
Author(s):  
К.Н. Волков ◽  
В.Н. Емельянов ◽  
И.В. Тетерина
Keyword(s):  
Gas Dynamics ◽  
Computational Gas Dynamics

Numerical and Experimental Study on Temperature Crossover in Shell and Tube Heat Exchangers

2011 ◽  
Vol 7 (4) ◽  
Author(s):  
Fuhua Jiang ◽  
Xianhe Deng
Keyword(s):  
Heat Transfer ◽  
Food Processing ◽  
Heat Exchangers ◽  
Heat Transfer Performance ◽  
Counter Flow ◽  
Numerical Studies ◽  
Shell And Tube ◽  
First Time ◽  
The Relationship ◽  
Dynamics Method

Experimental and numerical studies were conducted to investigate the heat transfer characteristics of five shell and tube heat exchangers (STHXs) with ratio of the length to width (L/W) at the range of 1.85 to 9.23. Temperature crossover in counter flow STHXs is meaningful in food processing industry. The relationship between temperature crossover and L/W is proposed for the first time. Both the experimental and numerical results show that temperature crossover can be achieved in STHXs with L/W?4.62 and can’t be achieved any more in STHXs with L/W?3.08. The results also indicate that heat transfer performance decreases with L/W decreasing. The inherent reason of this phenomenon is analyzed by computational fluid dynamics method.

Application of high-order accurate methods to solve the computational gas dynamics and aeroacoustics problems

2011 ◽  
Vol 54 (1) ◽  
pp. 34-42
Author(s):  
M. V. Usanin ◽  
A. A. Siner ◽  
A. M. Sipatov ◽  
L. Yu. Gomzikov ◽  
V. G. Avgustinovich
Keyword(s):  
Gas Dynamics ◽  
High Order ◽  
Computational Gas Dynamics
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