Introduction to Hypersonic Flow

Chernyi, G. G.; Seeger, Raymond J.

doi:10.1119/1.1941864

Cited by 36 publications

(17 citation statements)

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“…16, together with a discussion of assumptions that have been used by other workers in analyses of secondary injection phenomena, and a detailed derivation of the scaling law of Eq. (3) and its extension to a scaling law for the force on a flat plate.…”

Section: Scaling Laws For Side Force On a Wallmentioning

confidence: 99%

“…The origin of the coordinate system has been chosen so that the y = 0 plane includes the center of the injector and so that the origilllic,g at the intersection of the bow shock wave with the wall. For the purposes of this model it is assumed 1) that a sonie jet is injected into a uniform supersonic flow with no wall boundary layer, 2) that no mixing occurs between the injectant and either the primary flow or the separated flow near the injector, 3) that the interface between the injectant and primary flows is a quarter sphere followed by an axisymmetric half body, and 4) that the interface between the separated flow downstream of the injector and the injectant always lies inside the surface described in item 3. The force balance is made on the control volume formed by the quarter-spherical nose, which is located with one plane surface in the x-v plane and the other in the y-z plane. It is assumed 5) that the pressure forces on the sphere due to primary flow can be calculated by use of modified Newtonian flow, 6) that the injectant expands isentropically to the ambient pressure wjth its velocity parallel to the waH at the downstream face of the sphere, and 7) that the contribution to the momentum flux across the y-z plane due to flow in the separated region downstream of the injector can be neglected.…”

Section: Analytic Lvlodelmentioning

confidence: 99%

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Secondary injection of gases into a supersonic flow

1964

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The How field around the injection port for secondary injection of a gas nor:mal to a supersonic stream has been studied in a series of wind-tunnel experiments. The experiD1ents were conducted at freestream Mach numbers of 1.38 to 4.54. Gaseous nitrogen, argon, and helium were used as injectants. New information concerning pressure fields, concentration fields, and shock shapes was obtained. A scale pal'ameter has been calculated, based on a simple, inviscid model of the How field. This scale parameter gives a good general correlation of the data. Use of this scale parameter allows prediction of a simple scaling law for the side forces generated by secondary injection. This side-force scaling law is in approximate agreement with existing rocket motor test results.

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Section: Scaling Laws For Side Force On a Wallmentioning

confidence: 99%

Section: Analytic Lvlodelmentioning

confidence: 99%

Secondary injection of gases into a supersonic flow

1964

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“…These are the gasdynamic and free-molecular flows. In the gasdynamic limit, when Kn = 0, there hold the formulas of isentropic gas expansion in the centered expansion wave [8] x…”

Section: One-dimensional Solutionsmentioning

confidence: 99%

Rarefied gas deceleration in a channel in the case of expansion into a vacuum

2015

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The time-dependent problem of the development of a rarefied flow in a plane channel formed by two parallel infinite plates is considered on the basis of a kinetic model. At the initial moment of time the gas at rest occupies half the channel and borders on a vacuum. The effect of gas deceleration at the channel walls is studied as a function of the gas rarefaction degree under the conditions of the diffuse reflection of molecules from the boundary. Emphasis is placed on the calculations of the time dependence of the integral gas mass flux through the boundary separating the gas from the vacuum at the initial moment. The deceleration of the conditional expansion wave front and the conditional front of gas expansion into the vacuum is traced. The kinetic equation is numerically solved using a first-order difference method.

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“…The reason for this deformation of waveform is, at least in part, that the crest of the sound wave always has a higher temperature than the trough and thus travels faster than the trough. After a short distance X, the sound wave of large amplitude Ap and wavelength bears the following relationship to X: 26, as generated by the impact device used in our experiments, show that the saw-tooth or triangular waveform is typical of wave disturbances emanating from explosive bolt separation. Generation of Acoustic Disturbance by Impact of Gas Particles One way to determine the energy that is available for conversion into acoustic energy is to consider the work done by the exploded charge upon the inside walls of the bolt that contain the charge.…”

Section: Initial Stressmentioning

confidence: 97%

Apollo Launch Escape Tower Electroexplosive Bolts

Coffman¹,

Nussberger²

1966

IEEE Trans. Aerosp. Electron. Syst.

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Solid explosive detonation in direct contact with a metal body is examined to determine the energy transfer from latent chemical energy of an explosive into kinetic energy of the neighboring body structural members and spacecraft. Much of this is of an empirical nature since the time-dependent, three-dimensional problem involves extremely difficult analysis. Acoustic experiments were performed on a partially constructed spacecraft. A complete set of sound intensity maps was obtained. IntroductionThis study covers both an exploratory investigation of necessary charge and the evaluation of accompanying vibration and acoustic effects for spacecraft separation by explosive bolts. We will be concerned only with the main charge of RDX.From previous experiments reported, rough estimates were established for the range of sound disturbance intensity, which may be expected to occur within the Command Module upon separation from the escape tower. Searching the technical literature produced several papers which formed the basis for describing the sound disturbance waveform in the Command Module atmosphere. A Command Module was found which was partially assembled and suitable for acoustic experiments. Experiments were designed to form bases for establishing sound levels throughout the Command Module.

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Introduction to Hypersonic Flow

Cited by 36 publications

References 0 publications

Secondary injection of gases into a supersonic flow

Secondary injection of gases into a supersonic flow

Rarefied gas deceleration in a channel in the case of expansion into a vacuum

Apollo Launch Escape Tower Electroexplosive Bolts

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