A study of the pressure and heat transfer distribution on highly swept slab delta wings in supersonic flow

1966 ◽  
Author(s):  
J. PAULSEN ◽  
G. SCHADT
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow ◽  
Delta Wings

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

Numerical Simulation of Heat Transfer Enhanced Tube Inserted Delta-Wing

2014 ◽  
Vol 535 ◽  
pp. 66-70
Author(s):  
Chen Hong Zhao ◽  
Yong Gang Lei
Keyword(s):  
Heat Transfer ◽  
Numerical Simulation ◽  
Pressure Drop ◽  
Inclination Angle ◽  
Delta Wing ◽  
Delta Wings ◽  
Enhanced Tube ◽  
Delta Winglet

Heat transfer and resistance characteristics of a tube inserted delta-winglet (inclination angle is 10 °) are studied by numerical simulation. The results show that the delta-winglet enhance the heat transfer of the enhancement tube inserted delta-winglet and improve the PEC with modest pressure drop penalties. Compared with based tubes, the delta-wings structure enhance the heat transfer 19.52%-31%.

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.

Heat transfer in a supersonic flow

1973 ◽  
Vol 16 (12) ◽  
pp. 2129-2140 ◽  
Author(s):  
A.S. Predvoditelev
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow
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