Log in

Relevant bibliographies by topics / Jet exhaust plumes

Contents

Journal articles
Dissertations / Theses
Books
Book chapters
Conference papers

Academic literature on the topic 'Jet exhaust plumes'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Jet exhaust plumes.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Jet exhaust plumes"

1

Salemann, V., and J. M. Williams. "A New Method of Modeling Underexpanded Exhaust Plumes for Wind Tunnel Aerodynamic Testing." Journal of Engineering for Gas Turbines and Power 111, no. 4 (October 1, 1989): 748–54. http://dx.doi.org/10.1115/1.3240322.

Full text

Abstract:

A new method for modeling hot underexpanded exhaust plumes with cold model scale plumes in aerodynamic wind tunnel testing has been developed. The method is applicable to aeropropulsion testing where significant interaction between the exhaust and the free stream and aftbody may be present. The technique scales the model and nozzle external geometry, including the nozzle exit area, matches the model jet to free-stream dynamic pressure ratio to full-scale jet to free-stream dynamic pressure ratio, and matches the model thrust coefficient to full-scale thrust coefficient. The technique does not require scaling of the internal nozzle geometry. A generalized method of characteristic computer code was used to predict the plume shapes of a hot (γ = 1.2) half-scale nozzle of area ratio 3.2 and of a cold (γ = 1.4) model scale nozzle of area ratio 1.3, whose pressure ratio and area ratio were selected to satisfy the above criteria and other testing requirements. The plume shapes showed good agreement. Code validity was checked by comparing code results for cold air exhausting into a quiescent atmosphere to pilot surveys and shadowgraphs of model nozzle plumes taken in a static facility.

APA, Harvard, Vancouver, ISO, and other styles

2

Kärcher, B., and P. Fabian. "Dynamics of aircraft exhaust plumes in the jet-regime." Annales Geophysicae 12, no. 10/11 (August 31, 1994): 911–19. http://dx.doi.org/10.1007/s00585-994-0911-9.

Full text

Abstract:

Abstract. A computational model describing the two-dimensional, turbulent mixing of a single jet of exhaust gas from aircraft engines with the ambient atmosphere is presented. The underlying assumptions and governing equations are examined and supplemented by a discussion of analytical solutions. As an application, the jet dynamics of a B747-400 aircraft engine in cruise and its dependence on key parameters is investigated in detail. The computer code for this dynamical model is computationally fast and can easily be coupled to complex chemical and microphysical models in order to perform comprehensive studies of atmospheric effects from aircraft exhaust emissions in the jet regime.

APA, Harvard, Vancouver, ISO, and other styles

3

Kärcher, B., and P. Fabian. "Dynamics of aircraft exhaust plumes in the jet-regime." Annales Geophysicae 12, no. 10 (1994): 911. http://dx.doi.org/10.1007/s005850050114.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Dix, J., A. J. Saddington, K. Knowles, and M. A. Richardson. "Infra-red signature reduction study on a small-scale jet engine." Aeronautical Journal 109, no. 1092 (February 2005): 83–88. http://dx.doi.org/10.1017/s0001924000000580.

Full text

Abstract:

Abstract This paper presents infra-red signature data for a small-scale, low pressure ratio turbojet engine typical of that used in unmanned air vehicle applications. The aim of the study was to test a number of different convergent nozzle designs concentrating on those with trailing edge modifications. The engine used in the tests has a single stage centrifugal compressor and radial inflow turbine and is designed to produce approximately 150N of thrust at 103,500rpm using liquid propane fuel. The test rig consisted of a calibrated thrust stand whilst the engine was controlled through an electronic engine control unit and laptop PC. The jet plume was visualised using an infra-red spectroradiometer which yielded qualitative data across the infra-red spectrum. Simultaneous measurements were also made of the engine thrust. A Pitot probe was used to take pressure readings across different sections of the exhaust flow. Analysis of the infrared signature of the engine exhaust plume and any thrust penalty yielded a performance comparison for each of the nozzles tested. Correlation of engine thrust with engine rpm showed that, within the accuracy of the measurements, there was no significant thrust penalty associated with the notched nozzles. Infra-red imagery of the plain and 60° notched nozzles indicated that the latter reduced the length of the hottest part of the exhaust plume by approximately 33%. The spectroradiometer data shows a significant reduction in spectral radiance for the CO2 wavelength of approximately 4·3µm when the notched nozzles are used. The 60° notched nozzle appeared to perform best in reducing the spectral radiance at this wavelength. Centreline total pressure measurements in the exhaust plume correlated well with the infra-red imagery in that a potential core length reduction of up to 30% could be achieved using the 60° notched nozzle. Total pressure contours recorded 20mm (0·43D) downstream of the nozzle exit plane suggest that the notched nozzles are promoting increased mixing through radial spreading of the jet possibly associated with increased streamwise vorticity (although the latter could not be confirmed). There were also signs that the jet plumes being investigated were swirling.

APA, Harvard, Vancouver, ISO, and other styles

5

Nasuti, F., R. Niccoli, and M. Onofri. "A Numerical Methodology to Predict Exhaust Plumes of Propulsion Nozzles." Journal of Fluids Engineering 120, no. 3 (September 1, 1998): 563–69. http://dx.doi.org/10.1115/1.2820699.

Full text

Abstract:

A simple methodology to simulate the mixing layers that occur between nozzle exhaust jet and the external air is proposed. The method is based on a simplified model of the plume, that replaces the mixing layer with a contact discontinuity surface, thus avoiding the cumbersome calculation of the turbulent mixing of two flows with different chemical composition. The contact discontinuity is numerically treated by an advanced fitting technique, capable of tracking the discontinuity by points floating over the computational grid. The numerical method is discussed and its capability is demonstrated with validation tests, as well as with a discussion of some practical applications for underexpanded nozzle flows.

APA, Harvard, Vancouver, ISO, and other styles

6

Kärcher, B., and D. W. Fahey. "The role of sulfur emission in volatile particle formation in jet aircraft exhaust plumes." Geophysical Research Letters 24, no. 4 (February 15, 1997): 389–92. http://dx.doi.org/10.1029/97gl00119.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Gao, R. S., B. Kärcher, E. R. Keim, and D. W. Fahey. "Constraining the heterogeneous loss of O3on soot particles with observations in jet engine exhaust plumes." Geophysical Research Letters 25, no. 17 (September 1, 1998): 3323–26. http://dx.doi.org/10.1029/98gl02505.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Kärcher, B. "On the potential importance of sulfur-induced activation of soot particles in nascent jet aircraft exhaust plumes." Atmospheric Research 46, no. 3-4 (May 1998): 293–305. http://dx.doi.org/10.1016/s0169-8095(97)00070-7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Fisher, Edward M. D., Thomas Benoy, Gordon Humphries, David Wilson, M. Lengden, Walter Johnstone, Hugh McCann, et al. "A Custom, High-Channel Count Data Acquisition System for Chemical Species Tomography of Aero-Jet Engine Exhaust Plumes." IEEE Transactions on Instrumentation and Measurement 69, no. 2 (February 2020): 549–58. http://dx.doi.org/10.1109/tim.2019.2895932.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Takegawa, Nobuyuki, Yoshiko Murashima, Akihiro Fushimi, Kentaro Misawa, Yuji Fujitani, Katsumi Saitoh, and Hiromu Sakurai. "Characteristics of sub-10 nm particle emissions from in-use commercial aircraft observed at Narita International Airport." Atmospheric Chemistry and Physics 21, no. 2 (January 27, 2021): 1085–104. http://dx.doi.org/10.5194/acp-21-1085-2021.

Full text

Abstract:

Abstract. The characterization of ultrafine particle emissions from jet aircraft equipped with turbofan engines, which are commonly used in civil aviation, is an important issue in the assessment of the impacts of aviation on climate and human health. We conducted field observations of aerosols and carbon dioxide (CO2) near a runway at Narita International Airport, Japan, in February 2018. We used an ultrafine condensation particle counter (UCPC) and a condensation particle counter (CPC) with unheated and 350 ∘C heated operation modes to investigate the contributions of sub-10 nm size ranges to the total and the non-volatile particle number concentrations. The performance of the 350 ∘C heated mode was tested in the laboratory to verify the consistency with existing methods for non-volatile particle measurements. We also used a scanning mobility particle sizer with unheated and 350 ∘C heated modes and an engine exhaust particle sizer for the measurements of particle number size distributions. Spiked increases in the particle number concentrations and CO2 mixing ratios were observed to be associated with the directions of wind from the runway, which can be attributed to diluted aircraft exhaust plumes. We estimated the particle number emission indices (EIs) for discrete take-off plumes using the UCPC, CPC, and CO2 data. The median values of the total and the non-volatile particle number EIs for diameters larger than 2.5 nm as derived from the UCPC data were found to be 1.1×1017 and 5.7×1015 kg per fuel, respectively. More than half the particle number EIs were in the size range smaller than 10 nm for both the total and the non-volatile particles in most of the cases analyzed in this study. The significance of sub-10 nm size ranges for the total particles in the diluted plumes was qualitatively consistent with previous studies, but that for the non-volatile particles was unexpected. Possible factors affecting the similarities and differences compared with the previous findings are discussed.

APA, Harvard, Vancouver, ISO, and other styles

More sources

Dissertations / Theses on the topic "Jet exhaust plumes"

1

Cain, Terrence M. "An experimental study of under-expanded jets." Thesis, University of Oxford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.306018.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Welsh, Francis Paul. "Shock structure and stability in low density under-expanded jets." Thesis, University of Oxford, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.302489.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Jet exhaust plumes"

1

Falcovitz, Joseph. Spacecraft contamination from a chemical laser ring-jet: A progress report. Monterey, Calif: Naval Postgraduate School, 1985.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

2

Cusworth, Roland Alan. Turbulence structure of a premixed flame in a coaxial free air jet in the presence or absence of a base flow. [Toronto, Ont.]: Graduate Department of Aerospace Science and Engineering, University of Toronto, 1992.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

3

Jiang, L. Y. Turbulent mixing in supersonic high-temperature exhaust jets. North York, Ont: Institute for Aerospace Studies, University of Toronto, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

4

M, Myers Roger, and United States. National Aeronautics and Space Administration., eds. Pulsed plasma thruster contamination. [Washington, D.C: National Aeronautics and Space Administration, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

5

Final report for a preliminary investigation of Hall thruster technology: NAG3-1504. [Washington, DC: National Aeronautics and Space Administration, 1997.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Jet exhaust plumes"

1

Kirchheck, Daniel, Dominik Saile, and Ali Gülhan. "Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 145–62. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_9.

Full text

Abstract:

Abstract Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.

APA, Harvard, Vancouver, ISO, and other styles

2

Schumann, Ulrich. "Contrail Cirrus." In Cirrus. Oxford University Press, 2002. http://dx.doi.org/10.1093/oso/9780195130720.003.0015.

Full text

Abstract:

A contrail (a term introduced for “condensation trail” in 1942 by British pilots) is a visible cloud forming behind aircraft, mainly due to water vapor emissions from the engines. Contrails were first observed behind propeller-driven aircraft in 1915 but form as well from the exhaust of jet engines in cold ambient air (Schumann 1996a). Contrails are visible indicators of cruising aircraft and may impact the Earth's climate. Aircraft exhaust may influence cloud formation either directly by forming contrails or indirectly by causing an aerosol of black carbon soot, volatile particles, and metallic particles which later impact the formation and properties of cirrus clouds in the same air mass at other places. Though the cover by contrails is small compared to the cover by natural cirrus clouds, the potential climatic importance of contrails is being studied intensively. A review of the results obtained so far has been prepared for an assessment on Aviation and the Global Atmosphere (IPCC 1999). It reveals considerable progress in understanding aviation-produced aerosols and cloudiness (Fahey and Schumann 1999). Contrail studies also aid in learning about cirrus formation because contrails are cirrus clouds that form under relatively well defined and reproducible conditions. This chapter reviews some of the progress in understanding contrail formation, occurrence, properties, and radiative impact and identifies some important unanswered questions. Contrail formation can be accurately predicted for given atmospheric temperature and humidity conditions. Contrails form thermodynamically according to the Schmidt-Appleman criterion (Schmidt 1941; Appleman 1953) when the relative humidity (RH) in the plume of exhaust gases mixing with ambient air temporarily reaches or exceeds liquid saturation, so that liquid droplets form on cloud-condensation nuclei (CCN) and soon freeze to ice particles. Measurements have shown that liquid saturation is indeed necessary (see fig. 11.1) and that contrails do not form when the RH exceeds ice saturation (Jensen et al. 1998b; Kärcher et al. 1998a; Schumann et al. 2000). The maximum RH reaches liquid saturation when the ambient temperature is below a threshold temperature of typically -50° to -35°C, depending on ambient pressure and humidity and aircraft properties. This maximum is reached in the young plume (age <0.5 s) closely behind the aircraft.

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Jet exhaust plumes"

1

Fureby, Christer, Markus Henriksson, Oskar Parmhed, Lars Sjokvist, and Jon Tegner. "CFD Predictions of Jet Engine Exhaust Plumes." In 38th Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-3727.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

NELSON, H. "Infrared emission from jet engine exhaust plumes." In 24th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-465.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Nelson, Edward L., J. Robert Mahan, Jeffrey A. Turk, Robert R. Hardman, Larry D. Birckelbaw, and Paul A. Gelhausen. "Infrared characterization of jet engine exhaust plumes." In Optical Engineering and Photonics in Aerospace Sensing, edited by Wendell R. Watkins and Dieter Clement. SPIE, 1993. http://dx.doi.org/10.1117/12.151063.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Parmhed, Oskar, Henrik Edefur, Christer Fureby, Markus Henriksson, Shia-Hui Peng, Stefan Wallin, and Niklas Zettervall. "Simulating jet exhaust plumes for optical propagation calculations." In 45th AIAA Plasmadynamics and Lasers Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2492.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Dash, Sanford M. "Simulation of Laboratory Jets and Full Scale Exhaust Plumes (Keynote Paper)." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45056.

Full text

Abstract:

Recent activities at CRAFT Tech related to the simulation of high speed laboratory jets, their control via passive actuation, and the scale-up and revisions required for real engines and operation at flight are discussed. We focus on aircraft applications related to jet noise reduction with activities pertinent to varied missile jet/plume applications the subject of other review papers. Laboratory jet experiments have served to validate the RANS turbulence models utilized and are supplemented by LES studies to provide data sets not readily obtainable in the laboratory such as temperature fluctuation data needed for thermal transport modeling. Applications for a military fighter aircraft indicate that laboratory experiments cannot replicate the real exhaust environment and thus can only suggest actuation concepts that are promising. CFD is required to revise and scale-up these concepts for the real engine and to provide estimates of their performance in flight. Studies presented show the differences between laboratory plumes and real plumes, as well as the effects of plume/plume and plume/aerodynamic interactions which are quite appreciable and show a markedly different structure than that of the isolated jet under the same operating conditions.

APA, Harvard, Vancouver, ISO, and other styles

6

Martens, Steven, and Ludwig Haber. "Jet Noise Reduction for High Speed Exhaust Systems." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50455.

Full text

Abstract:

Jet noise has been an environmental issue since the advent of jet aircraft. The past five decades have seen much research into solving this very difficult challenge for a variety of applications. The Supersonic Transport (SST), High Speed Civil Transport (HSCT), and a variety of supersonic business jet (SSBJ) applications all face significant jet noise challenges. Jet noise from high performance military aircraft has also received growing attention. The continuous drive to higher specific thrust results in increasing jet noise levels. Compounding this is that many military bases, Naval in particular, are located in desirable locations on the coast, and surrounding communities are encroaching closer to these bases. In this paper we will conduct a survey of some jet noise reduction technologies for high-speed exhaust systems investigated in the past, as well as some of the implementation issues associated with them. Specific technologies aimed at changing the mixing characteristics of the jet plume after it leaves the nozzle will be discussed in detail, including chevrons and fluidic injection. Other noise reduction technologies, such as the inverted velocity profile, and fluid shield can also change the mixing characteristics of the jet plume. This includes the added benefit of noise reflection or shielding. Measured data will be presented to show the effect these technologies have on high-speed jets.

APA, Harvard, Vancouver, ISO, and other styles

7

Levy, Y., M. Lev, and V. Ovcharenko. "Infrared Radiation From Turbojet Exhaust Plume." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27379.

Full text

Abstract:

In recent years, there was an increasing interest in aircraft IR signature as an effective passive means of detecting and locking on to an aircraft. There are two main sources of the aircraft IR emission: engine-fuselage layout and gaseous exhaust plume. The size of aircraft plume is several times more than the size of aircraft. The present work focuses on the exhaust plume. The relatively high temperature plume ejected from the nozzle is a mixture of several species that are products of hydrocarbon fuel combustion under excess air condition: CO2, H2O, CO, O2, and N2. Experimental investigation of IR radiation from exhaust gases of a small turbojet engine was conducted in a micro jet engine SR-30 by Turbine Technologies, Ltd. The compact engine features a centrifugal flow compressor, reverse flow annular combustor and an axial flow turbine stage. The SR-30 follows the fundamental Brayton gas turbine cycle. The engine is operated at different regimes with various flow rates of air and kerosene. Measurements were obtained with engine operating at global equivalence ratio of about 0.23. The IR radiation images of the exhaust flow were obtained by a thermocamera equipped with a narrow bandpass filter that falls on the CO2 fundamental band emission. Temperature profiles were measured by a thermocouple in the exhaust flow. An in-house computer program was developed to calculate the IR emission from optically thick gas object and it takes into account the self-absorption of the IR radiation along a line-of-sight. An essential feature of the calculation is the fact that the optical path is non-isothermal. The typical IR spectrum of a turbo-jet engine exhaust flow was simulated using the developed computer program. The calculations allow prediction of “apparent” plume temperatures measured by the IR camera. The calculated results were compared with the experimental measurements and a good agreement was found.

APA, Harvard, Vancouver, ISO, and other styles

8

Devals, C., J. L. Estivalezes, G. Jourdan, and L. Houas. "Towards a Numerical Study of Two-Phase Flow Exhaust Plume Jet." In ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/fedsm2002-31028.

Full text

Abstract:

The aim of the present work is to determine experimental drag coefficients for spherical particles accelerated in shock-tube. Then, validations of two phase flow calculations dealing with solid propulsion rocket in supersonic flight are undertaken. First, experiments in the multi-phase vertical-horizontal shock-tube have been set up at IUSTI in Marseille. The drag coefficient is determinated for particle Reynolds numbers less than 50000 and for particle Mach numbers less than 1.14 and is compared with those found in literature. Second, calculation of two phase flow in solid rocket plume has been performed. The particles are tracked with a stochastic one-way coupling lagrangian method.

APA, Harvard, Vancouver, ISO, and other styles

9

Garmory, Andrew, Epaminondas Mastorakos, and Robert Bilger. "Simulations of the Chemical Transformations In a Jet Engine Exhaust Plume." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-429.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Castner, Raymond S., Khairul Q. Zaman, Amy Fagan, and Christopher Heath. "Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-0232.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!