Radiative Transport in Inviscid Nonadiabatic Stagnation-Region Shock Layers

Page, W. A.; Compton, D. L.; Borucki, W. J.; Ciffone, D. L.; Cooper, D.M.

doi:10.1016/b978-0-12-395735-1.50013-9

Cited by 18 publications

(9 citation statements)

References 18 publications

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“…5 shows that the dimensionless coefficient typically varies from C HR = 0.01 at v I = 10 km/sec to a saturation value of C HR ~ 0.1 for v I > 15 km/sec. C HR is a weakly increasing function of pressure, and an increasing function of the scale height of the gas layer.…”

Section: Thermal Loading and Ablationmentioning

confidence: 99%

“…If the incident stream is completely reduced to gas, then the flow field, i.e a shock standing off the surface, reduces to the case considered in Ref. 5. The total radiative power incident on the surface can be expressed as…”

Section: Thermal Loading and Ablationmentioning

confidence: 99%

“…Ref. 5 shows that the total radiative loss (into and away from the surface) is about 3S, or 30% of the incident power if C HR =0.1. This is the rationale for choosing ε =0.7 in section II.…”

Section: Thermal Loading and Ablationmentioning

confidence: 99%

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Mass Streams for Spacecraft Propulsion and Energy Generation

Hammer

2006

Journal of Propulsion and Power

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A speculative propulsion concept is presented, based on accelerating a spacecraft by impact of a stream of matter in relative motion with respect to the spacecraft. To accelerate the stream to the needed velocity the stream mass is contained in a transit vehicle, launched at low velocity and hence low energy cost, and then sent on a trajectory with near encounters of the planets for gravitational assist. The mass arrives at Earth or wherever the propellant is needed at much higher velocity and kinetic energy, where it is released into an extended stream suitable for propulsion. The stream, moving at a relative velocity in the range of 10 to 30km/s, should be capable of both high thrust and high specific impulse. Means of limiting the transverse expansion of the stream during release and for the ~ 1000 seconds duration of impact are a critical requirement for practicality of the concept. The scheme could potentially lead to a virtually unlimited energy source. One can imagine using a portion of one stream to launch another, larger payload on a similar trajectory. This creates, in effect, an energy amplifier extracting energy from the orbital motions of the planets. The gain of the energy amplifier is only limited by the capacity to prepare mass in transit vehicles. Nomenclature

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Section: Thermal Loading and Ablationmentioning

confidence: 99%

Section: Thermal Loading and Ablationmentioning

confidence: 99%

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Mass Streams for Spacecraft Propulsion and Energy Generation

Hammer

2006

Journal of Propulsion and Power

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“…Equations (1)(2)(3)(4) are the familiar body-oriented equations of motion transformed according to (6) Body-oriented coordinates are not convenient for unsteady analysis. This is due to the moving shock wave passing through the fixed mesh points causing differencing difficulties in the vicinity of the shock, and changing the number of mesh points used to describe the shock layer.…”

Section: Governing Equationsmentioning

confidence: 99%

“…(1)(2)(3)(4)(5) to center-line flow (r = 0), indeterminate expressions such as pu sinB/r have been evaluated with the aid of L' Hospital's rule.…”

Section: Governing Equationsmentioning

confidence: 99%

Coupled nongray radiating flows about long blunt bodies

Callis

1971

AIAA Journal

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Second-order time asymptotic solutions extending far downstream are presented for hypervelocity blunt-body flowfields including coupled nongray radiation. Shapes considered are sphere-cones and blunted conical shapes with continuous curvature. Numerical calculations treat the shock as a discrete surface, and it is assumed that the flow is inviscid, nonconducting, and axisymmetric. Thermochemical equilibrium is assumed. Radiation is accounted for with an eight-step model absorption coefficient including line, band, and continuum radiation. Results include shock shapes, radiative heating distributions, and profiles through the shock layer of pertinent thermodynamic and flow quantities. A parametric analysis is made of radiating flows over sphere-cones. Comparisons with other investigators are made, where possible. NomenclatureA,B,C,D,E = defined by Eq. (5) B v = nondimensional blackbody function 5 = speed of light, m/sec E n = exponential integral function of order n, E n (y) = e-y* t~n dt 9 h h P I v K k Pi,P* P -nondimensional divergence of the radiation flux vector = general parameter representing p,u, v, or p nondimensional enthalpy = Planck's constant, joule-sec = nondimensional specific radiation intensity = defined by Eqs. (5) = Boltzmann constant, joules/°K = defined by Eqs. (5) = nondimensional pressure = nondimensional radiative heat flux to body = nose radius, m f = nondimensional radial coordinate s = nondimensional radiation path length Presented as Paper 70-865 at

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Investigation of convective and radiative heating in hypersonic flow over blunt bodies

Golovachev¹

1972

Fluid Dyn

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Radiative Transport in Inviscid Nonadiabatic Stagnation-Region Shock Layers

Cited by 18 publications

References 18 publications

Mass Streams for Spacecraft Propulsion and Energy Generation

Mass Streams for Spacecraft Propulsion and Energy Generation

Coupled nongray radiating flows about long blunt bodies

Investigation of convective and radiative heating in hypersonic flow over blunt bodies

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