Radiation from rocket-exhaust plumes

Zirkind, Ralph

doi:10.1016/s0082-0784(67)80186-3

Cited by 6 publications

(4 citation statements)

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“…For a particle radiating at temperature, T, the fraction of energy emitted in the wavelength range between Aj_ and ^2 can be designated by (1) If, as we assume, the particle is cooling by radiation only, the energy radiated at T to cause a drop in temperature, dT, is just the change in enthalpy dH = C p (T) dTcal/mole (2) and the change in enthalpy due to radiation in the designated band is dH, 2 …”

Section: Radiant Power Formulamentioning

confidence: 99%

“…A significant part of the complete aerothermochemical analysis is the determination of the spectral radiance of particulate matter in the flame or plume. 1 ' 2 An essential problem in the analysis of particulate radiation is the determination of particle or cloud emissivity. Hence, quite a number of experimental and/or theoretical studies have been undertaken on the emissive or absorptive properties of particles of carbon 3 " 6 and oxides.…”

Section: Introductionmentioning

confidence: 99%

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Emission Spectra from a Stream of Cooling Particles

Rothwell

Schick

1974

Journal of Spacecraft and Rockets

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HYcm 2 -steradian-cm e(A) = spectral emissivity C p = molar heat capacity at constant pressure, cal/mole-°K W -mass flow rate, Ib/sec M = molecular weight, g/mole m = mass of particle, g A F = surface area of a particle, cm 2 E T -total radiant power from a particle r = particle radius, cm p = particle density, g/cm 3 e p = particle emissivity = Q a = ajnr 2 ff a = particle cross section for absorption, cm 2 m = complex index of refraction = n -jk n = real part of index of refraction k = imaginary part of index of refraction = extinction coefficient

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Section: Radiant Power Formulamentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Emission Spectra from a Stream of Cooling Particles

Rothwell

Schick

1974

Journal of Spacecraft and Rockets

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“…Since the 1940s, the infrared radiation emitted by aircraft engine exhaust plumes has become a subject of in-depth investigation [1] . The aircraft engine exhaust plumes is composed of high-temperature and high-pressure gases, these plumes radiate substantial thermal energy into space, yielding invaluable target information [2] , which has critical applications across various domains, encompassing sensor design, aircraft design and performance analysis, and target detection and tracking [3][4] .…”

Section: Introductionmentioning

confidence: 99%

Impacts of radiative heat transfer on the flow field and radiation of engine exhaust plumes

haiyan,

Weibiao,

Zhenhua

et al. 2024

Sixth Conference on Frontiers in Optical Imaging and Technology: Imaging Detection and Target Recognition

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Radiative heat transfer is a significant heat transfer mechanism in the formation of engine exhaust plumes, resulting in varied effects on the exhaust plume flow field and infrared radiation characteristics. In this work, simulation model is used to simulate exhaust plume flow of solid-propellant rocket motor, with consideration given to the recombination effects of 9 species and 10 elementary reactions. The study investigates the impact of radiative heat transfer on the exhaust plume flow field at different altitudes. Furthermore, a narrow-band model and the Line of Sight (LOS) approach are employed to calculate the infrared radiation characteristics of the flow field. It is indicated that radiative heat transfer affects the temperature of the flow field and the distribution of intermediate products such as CO and OH. Notably, at flight altitudes of 10km, the impact of radiative heat transfer is relatively weak, while at an altitude of 60km, the effect is more pronounced, which is attributed to the rarified air conditions prevalent in high-altitude regions, where molecular collisions are less frequent, thereby radiative heat transfer plays a significant role in heat conduction. Furthermore, radiative heat transfer also exerts a noticeable impact on the infrared characteristics of the flow field.

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“…The difference lies in the exponent, which ranges from 2.6 to 2.7, mostly owing to the variation in propellant type. The flight altitude and velocity of the rocket primarily impact the structure and morphology of the temperature components in the plume flow field and the afterburning effect, which in turn change the infrared radiation intensity of the target and the shape and size of the infrared radiation image [3,[9][10][11][12][13][14][15][16][17][18][19]. As the altitude of the target rises, the plume shape expands and grows broader and wider [19], with the afterburning effect decreasing [12], and the plume shows the phenomenon of afterburning cessation when it reaches 40-50 km.…”

Section: Introductionmentioning

confidence: 99%

Research on the Modeling Technique of Infrared Radiation Scaling Law for Rocket Engine Exhaust Plumes

Sun,

Niu,

Zhu

et al. 2024

Preprint

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The complexity of the rocket motor exhaust plume radiation phenomenon, along with the influence of numerous parameters and implicit propagation, makes the theoretical simulation calculations expensive. This hinders design optimization, parameter identification, and other studies. Hence, it is crucial to establish the direct correlation between thrust, velocity, altitude, detection angle, and plume radiation in engineering. The paper proposes a scaling law modeling approach for predicting plume infrared radiation from liquid oxygen (LOX)/kerosene rocket engines to solve the difficulties of quick prediction and lack of explicit models. An explicit scaling law model with four parameters is developed by utilizing the e-exponential scaling law to relate plume radiance to flight velocity, the power scaling law to relate plume radiance to vacuum thrust, and the sinusoidal scaling law to relate plume radiance to detection angle. This model employs a decoupled modeling approach for plume radiance, flight altitude, flight velocity, vacuum thrust, and detection angle. A fast prediction method for the LOX/kerosene rocket engine plume in the altitude range of 11~61 km is achieved. The theoretical simulation test shows the relative error of the velocity-scaling law in predicting the radiance of the RD-180 template engine during the Atlas III flight trajectory is less than 20%. The radiance of the RD-170 and RD-191 rocket engines is predicted using the thrust-scaling law based on the radiance of the RD-180 template engine exhaust plume. The radiance of the exhaust plume from the RD-170 and RD-191 rocket motors is estimated using the thrust-scaling law with an accuracy of under 15%. Subsequently, the radiance of these two motors at detection angles between 10° and 170° is predicted using the angle-scaling with a relative error of less than 35%.

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Radiation from rocket-exhaust plumes

Cited by 6 publications

References 0 publications

Emission Spectra from a Stream of Cooling Particles

Emission Spectra from a Stream of Cooling Particles

Impacts of radiative heat transfer on the flow field and radiation of engine exhaust plumes

Research on the Modeling Technique of Infrared Radiation Scaling Law for Rocket Engine Exhaust Plumes

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