High Temperature Thermal Conductivity of Rare Gases and Gas Mixtures

1968 ◽  
Vol 90 (3) ◽  
pp. 319-324 ◽  
Author(s):  
Richard A. Matula

The thermal conductivities of pure argon, pure xenon, and of three helium-argon mixtures have been determined in the temperature range 650–5000 deg K by measuring heat transfer rates from shock heated gases to the end wall of a shock tube. The heat transfer rate was measured by monitoring the time dependence of the voltage drop across a thin-film gage mounted in the end cap of the shock tube. During the course of the experiments, the pressure of the test gas behind the reflected shock wave ranged from approximately 1/3 to 2 atmospheres. In all cases, the temperature dependence (T) of the thermal conductivity (K) was assumed to follow a power law relationship of the form K/Kw = (T/Tw)b where Kw is the established value of the gas conductivity at the reference temperature (Tw) which was chosen near room temperature. The parameter b was evaluated by applying a least squares fit to the experimental data. Theoretical values of the conductivity of all of the gases studied were computed utilizing the Lennard-Jones (6–12) potential. In the case of the gas mixtures, an empirical combining rule was used to relate the force constants between unlike atoms to the known constants between like atoms. The experimental and theoretical results for the pure gases are in good agreement. The experimental and theoretical values of the mixture conductivities are within 10–20 percent, and as expected the theoretical predictions are least accurate for equimolar mixtures.

1965 ◽  
Vol 21 (4) ◽  
pp. 673-688 ◽  
Author(s):  
Morton Camac ◽  
Robert M. Feinberg

An infra-red heat-transfer gauge was used in a shock tube for end-wall measurements of the convective heat transfer from argon behind the reflected shock. The thermal conductivity of neutral (un-ionized) argon was measured before the ionization-relaxation time, and was fitted with the power-law temperature dependence 4·2 × 10−5(T/300)0·76±0·03cal/sec cm°K, whereTis measured in °K, and ±0·03 refers to the probable error The free-stream temperature ranged from 20,000 to 75,000°K, corresponding to incident-shock velocities from 3 to 6mm/μsec. At later times, after the free stream established equilibrium ionization, the convective-heat-transfer rate remained the same as the initial rate with neutral argon. Theoretical predictions of Fay & Kemp (1965), assuming equilibrium-boundary-layer conditions, are 20–30% below the experimental values. Also reported in this paper are measurements of the ionization times behind the reflected shock, and these are in agreement with an extrapolation of the Petschek & Byron (1957) measurements behind the incident shock. There is a discussion of the large changes in the gas conditions behind the reflected shock due to the ionization process. The final equilibrium conditions are reached abruptly, as indicated by the continuum-radiation emission which becomes constant immediately after ionization relaxation.


1965 ◽  
Vol 21 (4) ◽  
pp. 659-672 ◽  
Author(s):  
James A. Fay ◽  
Nelson H. Kemp

This paper deals with the calculation of the convective heat transfer rate to the end-wall of a shock tube from a monatomic gas heated by a reflected shock. We consider a range of shock strengths for which the equilibrium thermodynamic state is one of appreciable ionization. The resulting boundary-layer problem involves the thermal conductivity and ambipolar diffusion coefficient for a partially ionized monatomic gas. The formulation here is restricted to the case of a catalytic wall and equal temperatures for all species. We ignore the effect of the plasma sheath at the wall. Consideration is given to three limiting cases for which similarity-type solutions of the boundary-layer equations may be found: (1) complete thermodynamic equilibrium behind the reflected shock and within the boundary layer; (2) equilibrium behind the reflected shock, but no gas-phase recombination in the boundary layer; (3) no ionization in either region. Numerical calculations are carried out for argon using estimated values of thermal conductivity and ambipolar diffusion, and compared with shock-tube experiments of Camac & Feinberg (1965). For no ionization, calculations were made with thermal conductivity varying as the ¾ power of the temperature, which fits the estimates of Amdur & Mason (1958) up to 15,000°K. Excellent agreement with experiment is obtained confirming an extrapolation of this power law up to 75,000°K. For ionized cases, based on estimates of Fay (1964), the theory predicts heating rates 20–40% lower than measured values. Some possible reasons for this discrepancy are discussed.


2021 ◽  
Author(s):  
Harmanjit Singh Chopra

A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle. A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour. A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle.A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour.Experimental and numerical pressure-time profiles confirm the appearance of transient radial wave activity following the initial incidence of the normal shock wave on the convergence region of the nozzle. The results establish that the strength of this activity is markedly dependent upon the nozzle convergence wall angle and the location within the shock tube


2004 ◽  
Vol 52 (603) ◽  
pp. 153-159 ◽  
Author(s):  
Munetsugu Kaneko ◽  
Igor Men’shov ◽  
Yoshiaki Nakamura

2011 ◽  
Vol 83 ◽  
pp. 66-72 ◽  
Author(s):  
Vishakantaiah Jayaram ◽  
Singh Preetam ◽  
K. P. J. Reddy

Indigenously designed and fabricated free piston driven shock tube (FPST) was used to generate strong shock heated test gases for the study of aero-thermodynamic reactions on ceramic materials. The reflected shock wave at the end of the shock tube generates high pressure and temperature test gas (Argon, Ar) for short duration. Interaction of materials with shock heated Ar gas leads to formation of a new solid or stabilization of a material in new crystallographic phase. In this shock tube, the generated shock waves was utilized to heat Ar to a very high temperature (11760 K) at about 40-55 bar for 2-4 ms. We confirmed the phase transformation and electronic structure of the material after exposure to shock by XRD and XPS studies. This high enthalpy gas generated in the shock-tube was utilized to synthesize cubic perovskite CeCrO3from fluorite Ce0.5Cr0.5O2+δoxide. We were able to demonstrate that this ceramic materials undergoes phase transformations with the interaction of high enthalpy gas under shock dynamic loading.


2021 ◽  
Author(s):  
Harmanjit Singh Chopra

A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle. A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour. A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle.A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour.Experimental and numerical pressure-time profiles confirm the appearance of transient radial wave activity following the initial incidence of the normal shock wave on the convergence region of the nozzle. The results establish that the strength of this activity is markedly dependent upon the nozzle convergence wall angle and the location within the shock tube


1966 ◽  
Vol 88 (1) ◽  
pp. 52-55 ◽  
Author(s):  
D. J. Collins ◽  
W. A. Menard

The thermal conductivities of argon, neon, and krypton in the temperature range 1500 to 5000 deg Kelvin have been deduced from the measurement of heat transfer rates from the heated gases to the end wall in the reflected shock wave. Pressures ranged from approximately 1/2 atm to 3 atm. The relationship between thermal conductivity and temperature was assumed to be of the form k = aTb. The constant “b” was determined by a best fit to the data and the constant “a” by the known values of “k” below 1500 K. The effect of density variation in the thermal boundary layer was found to be significant in reducing the data; some previous investigations have neglected this effect.


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