scholarly journals Numerical investigation of the thermal-caloric imperfections on entropy enhancement across normal shock waves

2020 ◽  
Vol 48 (4) ◽  
pp. 285-308
Author(s):  
MEROUANE SALHI
Keyword(s):  
Shock Wave ◽  
Shock Waves ◽  
Molecular Size ◽  
Ideal Gas ◽  
Normal Shock ◽  
Wave Flow ◽  
Appreciable Effect ◽  
Real Gas ◽  
Normal Shock Wave ◽  
The Impact

Changes in flow properties across a normal shock wave are calculated for a real gas, thus giving us a better affinity to the real behavior of the waves. The purpose of this work is to develop shock-wave theory under the gaseous imperfections. Expressions are developed for analyzing the supersonic flow of such a thermally and calorically imperfect gas. The effects of molecular size and intermolecular attraction forces are used to correct a state equation, focusing on determination of the impact of upstream stagnation parameters on a normal shock wave. Flow through a shock wave in air is investigated to find a general form for normal shock waves. At Mach numbers greater than 2.0, the temperature rise is considerably below, and hence the density rise is well above, that predicted assuming ideal gas behavior. It is shown that caloric imperfections in air have an appreciable effect on the parameters developed in the processes considered. Computation of errors between the present model based on real gas theory and a perfect gas model shows that the influence of the thermal and caloric imperfections associated with a real gas is important.

Analysis of vibrational relaxation regions by means of the Rayleigh-line method

1961 ◽  
Vol 10 (1) ◽  
pp. 25-32 ◽  
Author(s):  
N. H. Johannesen
Keyword(s):  
Heat Transfer ◽  
Shock Wave ◽  
Shock Waves ◽  
Vibrational Relaxation ◽  
Ideal Gas ◽  
Relaxation Frequency ◽  
Rayleigh Line ◽  
Exact Methods ◽  
Real Gas ◽  
Density Distributions

The physics of shock-waves with vibrational relaxation regions is recapitulated, and it is shown that exact methods of analysis can be developed from the classical Rayleigh-line equations by treating the real gas as an ideal gas with heat transfer. By using these methods to analyse experimental records of density distributions in relaxation regions, a large number of local values of the relaxation frequency, rather than a single over-all value, may be obtained from each shock-wave record.

Normal shock-wave properties in imperfect air and nitrogen

AIAA Journal ◽  
1965 ◽  
Vol 3 (3) ◽  
pp. 554-556 ◽  
Author(s):  
CLARK H. LEWIS ◽  
E. G. BURGESS
Keyword(s):  
Shock Wave ◽  
Normal Shock ◽  
Normal Shock Wave ◽  
Wave Properties

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Jeyakumar Suppandipillai ◽  
Jayaraman Kandasamy ◽  
R. Sivakumar ◽  
Mehmet Karaca ◽  
Karthik K.
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Pressure Loss ◽  
Total Pressure ◽  
Injection Pressure ◽  
Total Pressure Loss ◽  
Normal Shock ◽  
Content Type ◽  
Normal Shock Wave ◽  
Scramjet Combustor

Purpose This paper aims to study the influences of hydrogen jet pressure on flow features of a strut-based injector in a scramjet combustor under-reacting cases are numerically investigated in this study. Design/methodology/approach The numerical analysis is carried out using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport k-ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters such as the shock wave pattern, wall pressures and static temperature across the combustor are validated with the reported experiments. The results comply with the range, indicating the adopted simulation method can be extended for other investigations as well. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency and total pressure loss. Findings The results revealed that the augmentation of hydrogen jet pressure via variation in flame features increases the static pressure in the vicinity of the strut and destabilize the normal shock wave position. Indeed, the pressure of the mainstream flow drives the shock wave toward the upstream direction. The study perceived that once the hydrogen jet pressure is reached 4 bar, the incoming flow attains a subsonic state due to the movement of normal shock wave ahead of the strut. It is noticed that the increase in hydrogen jet pressure in the supersonic flow field improves the jet penetration rate in the lateral direction of the flow and also increases the total pressure loss as compared with the baseline injection pressure condition. Practical implications The outcome of this research provides the influence of fuel injection pressure variations in the supersonic combustion phenomenon of hypersonic vehicles. Originality/value This paper substantiates the effect of increasing hydrogen jet pressure in the reacting supersonic airstream on the performance of a scramjet combustor.

Accuracy analysis of DSMC chemistry models applied to a normal shock wave

2012 ◽  
Author(s):  
Sergey Gimelshein ◽  
Ingrid Wysong ◽  
Yevgeny Bondar ◽  
Mikhail Ivanov
Keyword(s):  
Shock Wave ◽  
Normal Shock ◽  
Accuracy Analysis ◽  
Normal Shock Wave

Refraction of a normal shock wave from nitrogen into polyurethane foam

1990 ◽  
Author(s):  
L. F. Henderson ◽  
R. J. Virgona ◽  
J. Di ◽  
L. G. Gvozdeva
Keyword(s):  
Shock Wave ◽  
Polyurethane Foam ◽  
Normal Shock ◽  
Normal Shock Wave
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