scholarly journals Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow

2020 ◽  
Author(s):  
Dimitrios P. Spiridakos ◽  
Nicholas C. Markatos ◽  
Despoina Karadimou
Keyword(s):  
Mathematical Modeling ◽  
Supersonic Flow ◽  
Pressure Distribution ◽  
Aerodynamic Heating

scholarly journals Calculation of Toxic Substance Burning with Formation of Combustion Products’ Vertical Supersonic Stream

2016 ◽  
Vol 5 (6) ◽  
pp. 30-37
Author(s):  
Дорофеев ◽  
A. Dorofeev ◽  
Бурцев ◽  
I. Burtsev
Keyword(s):  
Mathematical Modeling ◽  
Supersonic Flow ◽  
Rocket Engine ◽  
Toxic Substance ◽  
Combustion Products ◽  
Liquid Rocket Engine ◽  
Supersonic Stream ◽  
Gas Dynamic ◽  
Liquid Rocket ◽  
The One

A system for burning of a destroyed highly toxic substance with formation of a vertical supersonic stream of combustion products moved away to the atmosphere on considerable heights has been considered. A technique and an algorithm for conjugated gas-dynamic and thermodynamic calculation of working processes in two-zonal unit with primary burning using air in a camera similar to the one of a liquid rocket engine, and after-burning in a supersonic flow have been proposed. The technique has been approved on the examples of after-burning mathematical modeling and a parametrical research on combustion completeness influence on composition and properties of products resulting from heptyl combustion in air with after-burning in case of methane supply in the second zone.

scholarly journals Aerodynamic Layout Designs Using of Microflaps for Flow Control of a Supersonic Finned Projectile

2019 ◽  
Vol 37 (2) ◽  
pp. 344-353
Author(s):  
Xiaopeng Li ◽  
Shun Kang ◽  
Tianming Wang ◽  
Yangzheng Zhao
Keyword(s):  
High Pressure ◽  
Control System ◽  
Supersonic Flow ◽  
Flow Control ◽  
Pressure Distribution ◽  
Surface Pressure ◽  
Pressure Zone ◽  
Bow Shocks ◽  
Flow Control System ◽  
Interference Mechanism

In this paper, the flow control system consists of some small microflaps located between the rear fins of the projectile. These microflaps can alter the flow field in the finned region of the projectile resulting in asymmetric pressure distribution and thus producing control forces and moments, furthermore to provide directional control for a supersonic projectile. Due to the small size and high speed characteristics of projectile, which is with fast and valid response characteristics, this flow control system has initially shown excellent potential in terms of supersonic flow control. The CFD simulation used here solves steady-state Reynolds-averaged Navier-Stokes equation with two-equation turbulence model k-ε. Firstly, we investigate the flow mechanism around microflap in supersonic flow, the flow fields around the microflap are complex, involving three-dimensional shock-shock, shock-boundary layer interactions. Secondly, for the microflap and the fin of Basic Finner configuration, the influence of microflap geometric parameters, microflap locations on aerodynamics is obtained and the interference mechanism is explored. Finally, several typical roll and pitch control layouts are described. According to the simulation results and their analysis, some preliminary conclusions can be drawn: by analyzing the flow interference mechanism between microflap and the fin, we find that the separated shocks ahead of the microflap, the bow shocks around microflap, and the trailing-edge wake, have influences on fin's surface pressure; among these factors, the bow shocks are stronger than separated shocks, furthermore it can generate larger high pressure region. Then we find out the aerodynamic characteristics of several typical control layouts at a supersonic speed, Ma=2.5, furthermore, hence nearly 4.8% drag is increase compared with the condition without microflap. As the number of microflaps increasing, the control aerodynamic forces and moments increases almost linearly. With a proper layout of the microflap's location, quick change in the surface pressure distribution can be achieved for rear fins of the projectile, the microflap should be mounted that can increase the high pressure zone, meanwhile, reduce the low pressure zone on the surface of fins, thus modulating the projectile's attitude can be realized.

Calculation of the Flow Properties Up- and Downstream of and Within a Supersonic Turbine Cascade

1972 ◽  
Author(s):  
O. K. Lawaczeck
Keyword(s):  
Supersonic Flow ◽  
Wind Tunnel ◽  
Pressure Distribution ◽  
Theoretical Method ◽  
Experimental Results ◽  
Turbine Cascade ◽  
Flow Properties ◽  
Flow Through

This paper deals with the flow through cascades, which have a supersonic flow up- and downstream. A theoretical method is described to calculate, under certain conditions, the flow quantities up- and downstream of and within the cascade and to determine the pressure distribution on the blades. The method is compared with experimental results, carried out in the cascade wind tunnel of the Aero dynamische Versuchsanstalt Göttingen (AVA), Germany.

scholarly journals Mathematical modeling of groundwaters pressure distribution in the underground structures by cylindrical form zone

2018 ◽  
Vol 196 ◽  
pp. 02025 ◽  
Author(s):  
Valeriy Telichenko ◽  
Vladimir Rimshin ◽  
Vladimir Eremeev ◽  
Vladimir Kurbatov
Keyword(s):  
Mathematical Modeling ◽  
Mathematical Model ◽  
Pressure Distribution ◽  
Underground Structure ◽  
Viscosity Coefficient ◽  
Soil Porosity ◽  
Cylindrical Shape ◽  
Underground Structures ◽  
Cylindrical Form ◽  
Analytical Formulas

A mathematical model is developed for studying the distribution of groundwater pressure and its variation in the zone of underground structures of a cylindrical shape. Based on the created model, the influence of the thickness of the aquifer, the soil porosity, the filtration coefficient, the viscosity coefficient and the piezoelectric conductivity coefficient on the pressure that groundwater exerts on the lower part of the underground structure is investigated. The analysis of the possibility of pushing the structure and breaking the foundation under the influence of pressure caused by groundwater is analyzed. Analytical formulas are obtained for estimating the stresses in the foundation and predicting the possibility of its destruction.

Influence of Thermal Protection Material Composition on Heat and Mass Exchange of Body in Spatial Supersonic Flow

2016 ◽  
Vol 683 ◽  
pp. 142-149
Author(s):  
Victor D. Goldin ◽  
Vyacheslav A. Ovchiinikov ◽  
Ivan A. Kotov
Keyword(s):  
Supersonic Flow ◽  
Surface Temperature ◽  
Mass Exchange ◽  
Thermal Protection ◽  
Conjugate Problem ◽  
Material Composition ◽  
Aerodynamic Heating ◽  
Carbon Cloth ◽  
Supersonic Speed ◽  
Heat And Mass Exchange

The conjugate problem of aerodynamic heating of a blunted cone moving in the atmosphere at angle of attack at supersonic speed is considered. Three modifications of a thermal protection material based on coal-plastic with different proportions of a phenol-formalhyde binder and a carbon cloth are investigated. The effect of the material composition on the surface temperature and the mass loss characteristics is analyzed.

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