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2 edition of Shock tube simulation of entry stagnation conditions in planetary gases found in the catalog.

Shock tube simulation of entry stagnation conditions in planetary gases

M. J. Lewis

Shock tube simulation of entry stagnation conditions in planetary gases

by M. J. Lewis

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Published in [Rhode-Saint-Genèse] .
Written in English

    Subjects:
  • Shock tubes.

  • Edition Notes

    Statementby M.J. Lewis.
    SeriesTechnical note -- 77, Technical note (Von Karman Institute for Fluid Dynamics) -- 77.
    The Physical Object
    Pagination1 v. ;
    ID Numbers
    Open LibraryOL19272078M

    The probe has experienced the most severe entry conditions in a planet of our solar system. As a matter of fact, Galileo entered into the atmosphere with a relative velocity of km/s and during the deceleration from M the peak heating rate and heat load exerted on the forebody heatshield amounted to M W / m 2 and 3 M J / m 2 Cited by: 1. The numerical simulation of unsteady shock-wave/boundary-layer interactions in reacting gas mixtures. Author Index. Keyword Index. Volume II. Chemical Physics. UV- and IR-absorption measurements in a shock tube using multiple reflections. High-temperature thermolysis of ethylene-d 4. Single-pulse shock-tube study of tetraethoxysilane decomposition.

      Parallel calculations within the framework of the direct simulation Monte Carlo method were performed on multiprocessor computers using the block decomposition of the simulation region. At the initial moment, the driver section of the shock was filled with a gas with a molecular mass identical to that of H2 while the driven section was filled with a mixture of gases with molecular masses Cited by: 2. Book — 1 online resource (p. ): digital, PDF file. Application of program LAURA to perfect gas shock tube flows [microform]: a parametric study [] Shock tube simulation of entry stagnation conditions in planetary gases [] Lewis, M. J. [Rhode-Saint-Genèse]

      The simulation of the shock tube to the secondary diaphragm calculations use the geometry and fill conditions described (2, cells axially, cells radially, wall/throat clustered) in Section 2, an ideal mixture of perfect gas (reservoir and started m from the primary diaphragm, using transient driver gas) and equilibrium gas (shock. Plasma wind tunnel experiments have been performed simulating a Hayabusa reentry trajectory point at km altitude with a velocity of km / s corresponding to a local mass–specific enthalpy of MJ / kg and a stagnation pressure of kPa. Ablation–radiation coupling is investigated using a carbon preform sample, a lightweight carbon phenolic ablator sample, and cooled by: 5.


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Shock tube simulation of entry stagnation conditions in planetary gases by M. J. Lewis Download PDF EPUB FB2

In this work, the direct simulation Monte Carlo (DSMC)4 technique is utilized to simulate a 1D normal hypersonic shock wave in an 89%% H 2-He mixture as measured in the EAST shock tube. This hypersonic shock wave is comparable to the stagnation line quantities experienced during Saturn entry scenarios.

To match the DSMC. Arc Shock Tube (EAST) at the NASA Ames Research Center were performed for a range of Saturn entry trajectory conditions.

3 These tests were performed in a hydrogen-helium mixture (89%% by volume) for a set of freestream. instance, the thermodynamic state of the gas at the stagnation point of a blunt model in the shock tube flow behind an incident shock wave moving at 29, ft/sec is equivalent to flight stagnation conditions at a speed of 40, ft/sec.

For Producing such high shock velocities. Direct Simulation Monte Carlo Shock Simulation of Saturn Entry Probe Conditions Article in Journal of Thermophysics and Heat Transfer 32(6). Using an expansion tube, this paper investigates how increasing the percentage of helium in the H 2 / He test gas, or substituting the helium for the heavier noble gas neon, can be used to generate representative shock-layer conditions associated with Uranus and Saturn entry.

Theoretically, it was found that either test gas substitution should Author: Christopher M. James, David E. Gildfind, Richard G.

Morgan, Steven W. Lewis, Timothy J. McIntyre. The main regularities of the formation of conditions behind the reflected shock wave in a shock tube in presence of chemical reactions are studied. The dependence of the parameters of supersonic flows on the conditions at the nozzle inlet is by: 1.

Shock tubes are capable of simulating the high velocity and low density conditions typical of planetary entry and thus are able to recreate. A stagnation streamline model incorporating quantum-state-resolved chemistry is proposed to study hypersonic nonequilibrium flows along the stagnation streamline.

the calculated distributions agree well with the measurement data of a shock tube experiment for the dissociation and vibrational “ Planetary-entry gas dynamics,” Annu.

Shock tube simulation. Introduction. In this project we will simulate the shock tube using converge simulation. Shocks are one of the important phenomena for the engineering design as especially in aerodynamics, recently shocks were more closely researched in the automotive industry for developing new i.c.

engines technologies. The hyper-velocity shock tube (HVST) simulates the thermochemical properties in the shock layer of hypersonic systems in flight, while the hyper-velocity expansion tube (HVET) reproduces those in. Thus the expansion tube is able to generate high velocity cold flows for direct simulation of the conditions of planetary entry.

Typical test times available are on the order of several hundred microseconds. A more complete discussion of the theories of operation and of operational experiences for expansion tubes may be found in refs.

Author: Walter B. Olstad. Results are presented of a numerical calculation of an unsteady two-dimensional axisymmetric wave flow of an inert monodispersed gas suspension from the channel of a shock tube into the surrounding gaseous space under the action of a gas compressed in a high-pressure chamber.

The acceleration of dispersed particles inside the tube and in the submerged space behind the diffracting air shock Author: A. Kutushev, A. Tatosov. Normal shocks are produced in the Electric Arc Shock Tube with freestream pressures of Torr and velocities from km/s.

heating models.1{3 The shock tube produces high velocity gas ows with compositions and densities relevant to planetary entry. These conditions are achieved by creating a sudden pressure discontinuity which moves hypersonically into the gas in front of it, in the form of a normal shock.

Abstract. Further exploration of the four gas giants in our solar system, Jupiter, Saturn,Uranus, and Neptune, is important for many reasons. The gas giants contain matter produced during the formation of the solar system that is thought to hold valuable clues about the origins of life [9]; Saturn’s moon Titan is the only moon in our solar system with its own atmosphere (which the Huygens Cited by: 4.

Shock waves are generated in the NASA Ames Electric Arc Shock Tube (EAST) facility at velocities from km/s and freestream densities from × kg/m3 ( Torr, corresponding to. Use of Real Gases in a Shock Tube (Report ) [Engineering Research Institute] on *FREE* shipping on qualifying offers.

Use of Real Gases in a Shock Tube (Report )Author: Engineering Research Institute. of using these sensors on shock tube improvement since they can detect high temperature air with an appropriate response time.

Shock tubes are used for the simulation of the flight conditions of high speed flight, for example, atmospheric vehicle reentry. In fact, this kind of facility can create high stagnation temperature and pressure, through aAuthor: Rafael Augusto Cintra, Tiago Cavalcanti Rolim, Bruno Coelho Lima.

generation of gas giant entry probes. The expansion tube, a modified shock tube that uses an extra low pressure shock tube to accelerate the shocked test gas to superorbital planetary entry conditions (through an unsteady expansion), typically between 6–15 km/s, is potentially well suited for simulating entry for planned missions to Uranus.

area shock tube having a helium drive and air, C02, N2, or A as test gases. Driver conditions are varied to include pressures from 10 to 1, atm and tem­ peratures from ' to 10,OOOo K.

Substantial deviations from the perfect-gas results are found for tailored Mach numbers greater than 8. For a given reservoir or reflected-shock enthalpy, real-gas effects may reduce driver tem­File Size: 2MB. 3. Shock‐Tube Results [7] Shock‐tube experiments were carried out at NASA Ames by Bose et al.

for conditions representative of a Titan aerocapture trajectory at velocities 5–9 km s −1. During the test campaign, Titan's atmosphere was anticipated to be composed of nitrogen with small amounts of methane (2–5% per volume) and argon (0 Cited by: Abstract.

The Galileo probe’s km/s entry into Jupiter on December 7th,was an engineering triumph. The probe survived entry into the atmosphere of the largest gas giant planet in the solar system, and completed its full scientific : C. M. James, D. E. Gildfind, R. G. Morgan, S. W. Lewis, T. M. McIntyre.Physical Description of the Shock Tube Problem The fundamental idea of the shock tube is the following: consider a long one-dimensional (1D) tube, closed at its ends and divided into two equal regions by a thin diaphragm (see Fig.

). Each region is filled with the same gas, but with different thermodynamic parameters (pressure, density,File Size: KB.