MHD deceleration and heat transfer for a sphere in a supersonic flow of partially ionized gas

1991 ◽  
Vol 32 (1) ◽  
pp. 12-15 ◽  
Author(s):  
V. V. Gubin ◽  
V. A. Shuvalov
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow ◽  
Ionized Gas ◽  
Partially Ionized

Heat Transfer from a Partially Ionized Gas to a Gaseous Coolant

1963 ◽  
Author(s):  
Peter M. Williams ◽  
Martin P. Sherman ◽  
Paul F. Jacobs
Keyword(s):  
Heat Transfer ◽  
Ionized Gas ◽  
Gaseous Coolant ◽  
Partially Ionized

Heat Transfer From Partially Ionized Gases in the Presence of an Axial Magnetic Field

1962 ◽  
Vol 84 (2) ◽  
pp. 169-176 ◽  
Author(s):  
V. J. Raelson ◽  
P. J. Dickerman
Keyword(s):  
Magnetic Field ◽  
Heat Transfer ◽  
Field Strength ◽  
Axial Magnetic Field ◽  
Plasma Generator ◽  
Ionized Gas ◽  
Test Channel ◽  
Boundary Layer Region ◽  
Partially Ionized ◽  
Layer Region

This work was performed in order to investigate the influence of an axial magnetic field on the flow properties and heat-transfer characteristics of a partially ionized gas in a cylindrical flow channel. A description of the plasma generator and test channel is given along with experimental results for heat-transfer measurements at the channel wall and flow conditions within the channel as a function of field strength. Data obtained show a heat-flux reduction to the walls of the order of 20 per cent for a field strength of 20 kilogauss with indications that the interaction is limited to the boundary-layer region.

Partially Ionized Gas Flow and Heat Transfer in the Separation, Reattachment, and Redevelopment Regions Downstream of an Abrupt Circular Channel Expansion

1972 ◽  
Vol 94 (1) ◽  
pp. 119-127 ◽  
Author(s):  
L. H. Back ◽  
P. F. Massier ◽  
E. J. Roschke
Keyword(s):  
Heat Transfer ◽  
Gas Flow ◽  
Reverse Flow ◽  
Vortex Sheet ◽  
Good Prediction ◽  
Ionized Gas ◽  
Energy Fraction ◽  
High Enthalpy ◽  
Channel Expansion ◽  
Partially Ionized

Heat transfer and pressure measurements obtained in the separation, reattachment, and redevelopment regions along a tube and nozzle located downstream of an abrupt channel expansion are presented for a very high enthalpy flow of argon. The ionization energy fraction extended up to 0.6 at the tube inlet just downstream of the arc heater. Reattachment resulted from the growth of an instability in the vortex sheet-like shear layer between the central jet that discharged into the tube and the reverse flow along the wall at the lower Reynolds numbers, as indicated by water flow visualization studies which were found to dynamically model the high-temperature gas flow. A reasonably good prediction of the heat transfer in the reattachment region where the highest heat transfer occurred and in the redevelopment region downstream can be made by using existing laminar boundary layer theory for a partially ionized gas. In the experiments as much as 90 percent of the inlet energy was lost by heat transfer to the tube and the nozzle wall.

Heat transfer at the nose of a blunt body in a rarefied supersonic flow of a nitrogen-hydrogen mixture

1975 ◽  
Vol 14 (6) ◽  
pp. 809-812 ◽  
Author(s):  
A. A. Bochkarev ◽  
V. A. Kosinov ◽  
V. G. Prikhod'ko ◽  
A. K. Rebrov
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow ◽  
Blunt Body ◽  
Hydrogen Mixture

Base heat transfer in an axisymmetric supersonic flow

AIAA Journal ◽  
1970 ◽  
Vol 8 (5) ◽  
pp. 974-976 ◽  
Author(s):  
LEROY S. FLETCHER
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow ◽  
Axisymmetric Supersonic Flow

Computational study of unsteady gas flow in the combustion chamber of a ramjet engine with heat transfer

2021 ◽  
pp. 50-61
Author(s):  
Надежда Петровна Скибина
Keyword(s):  
Heat Transfer ◽  
Numerical Simulation ◽  
Supersonic Flow ◽  
Combustion Chamber ◽  
Gas Flow ◽  
Stokes Equations ◽  
Heat Conducting ◽  
Measuring Device ◽  
Ramjet Engine ◽  
Mach Numbers

Проведено численное исследование нестационарного турбулентного сверхзвукового течения в камере сгорания прямоточного воздушно-реактивного двигателя. Описана методика экспериментального измерения температуры на стенке осесимметричного канала в камере сгорания двигателя. Математическое моделирование обтекания исследуемой модели двигателя проводилось для скоростей набегающего потока M = 5 ... 7. Начальные и граничные условия задачи соответствовали реальному аэродинамическому эксперименту. Проанализированы результаты численного расчета. Рассмотрено изменение распределения температуры вдоль стенки канала с течением времени. Проведена оценка согласованности полученных экспериментальных данных с результатами математического моделирования. Purpose. The aim of this study is a numerical simulation of unsteady supersonic gas flow in a working path of ramjet engine under conditions identical to aerodynamic tests. Free stream velocity corresponding to Mach numbers M=5 ... 7 are considered. Methodology. Presented study addresses the methods of physical and numerical simulation. The probing device for thermometric that allows to recording the temperature values along the wall of internal duct was proposed. To describe the motion of a viscous heat-conducting gas the unsteady Reynolds averaged Navier - Stokes equations are considered. The flow turbulence is accounted by the modified SST model. The problem was solved in ANSYS Fluent using finite-volume method. The initial and boundary conditions for unsteady calculation are set according to conditions of real aerodynamic tests. The coupled heat transfer for supersonic flow and elements of ramjet engine model are realized by setting of thermophysical properties of materials. The reliability testing of numerical simulation has been made to compare the results of calculations and the data of thermometric experimental tests. Findings. Numerical simulation of aerodynamic tests for ramjet engine was carried out. The agreement between the results of numerical calculations and experimental measurements for the velocity in the channel under consideration was obtained; the error was shown to be 2%. The temperature values were obtained in the area of contact of the supersonic flow with the surface of the measuring device for the external incident flow velocities for Mach numbers M = 5 ... 7. The process of heating the material in the channel that simulated the section of the engine combustion chamber was analyzed. The temperature distribution was studied depending on the position of the material layer under consideration relative to the contact zone with the flow. Value. In the course of the work, the fields of flow around the model of a ramjet engine were obtained, including the region of supersonic flow in the inner part of axisymmetric channel. The analysis of the temperature fields showed that to improve the quality of the results, it is necessary to take into account the depth of the calorimetric sensor. The obtained results will be used to estimate the time of interaction of the supersonic flow with the fuel surface required to reach the combustion temperature.

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