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Автор: Grafiati
Опубліковано: 6 вересня 2023

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Статті в журналах з теми "Blunt body"

1

Hollis, Brian R., and Salvatore Borrelli. "Aerothermodynamics of blunt body entry vehicles." Progress in Aerospace Sciences 48-49 (January 2012): 42–56. http://dx.doi.org/10.1016/j.paerosci.2011.09.005.

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2

Li, Yong Hong, Xin Wu Tang, and Wei Qun Zhou. "Aerodynamic and Numerical Study on the Influence of Spike Shapes at Mach 1.5." Advanced Materials Research 1046 (October 2014): 177–81. http://dx.doi.org/10.4028/www.scientific.net/amr.1046.177.

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Анотація:
Taking into account the issue of configuration or aerodynamic heating, most supersonic and hypersonic flight vehicles have to use the blunt-nosed body. However, in supersonic especially in hypersonic flow the strong bow shock ahead of the blunt nose introduces a rather high shock drag that affects the aerodynamic performance of the vehicles seriously. A spike mounted on a blunt body during its flight pushes the strong bow shock away from the body surface and forms recirculation flow with low pressure ahead of the body surface, and then decreases the drag. The drag reduction effects of spikes in high supersonic and hypersonic flow had been validated through experimental and numerical methods. In order to analyze the influence of the spike on aerodynamic characteristics at low supersonic (M=1.5) flow past blunt-nosed bodies, numerical studies were carried out which included the influence of the spike shape, the analysis of the fluid flow structures and the effect on the aerodynamic characteristics of a blunt body.
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3

Watanabe, Yasumasa, Kojiro Suzuki, and Ethirajan Rathakrishnan. "Aerodynamic characteristics of breathing blunt nose configuration at hypersonic speeds." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 5 (April 19, 2016): 840–58. http://dx.doi.org/10.1177/0954410016643979.

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Breathing blunt nose technique is one of the promising methods for reducing the drag of blunt-nosed body at hypersonic speeds. The air, traversed by the bow shock positioned ahead of the nose, at the stagnation region is allowed to enter through a hole at the blunt-nose and ejected at the rear part (base region) of the body. This manipulation reduces the positive pressure over the stagnation regions of the nose and increases the pressure at the base, resulting in reduced suction at the base. The simultaneous manifestation of reducing the compression at the nose and suction at the base regions results in reduction of the total drag. The drag reduction caused by the breathing blunt nose technique has been measured in a Mach 7 tunnel. Also, the drag and flow field around the blunt-nosed body, with and without breathing hole, has been computed. The aerodynamic characteristics of the breathing blunt nose model obtained experimentally are compared with the CFD results. It is found that the breathing results in 5% reduction in drag. The lift coefficient also comes down for the model with breathing nose. But the lift-to-drag ratio is found to be the same for both the cases; the blunt-nosed body with and without nose-hole.
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4

Kazemba, Cole D., Robert D. Braun, Ian G. Clark, and Mark Schoenenberger. "Survey of Blunt-Body Supersonic Dynamic Stability." Journal of Spacecraft and Rockets 54, no. 1 (January 2017): 109–27. http://dx.doi.org/10.2514/1.a33552.

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5

Shang, J. S., J. Hayes, J. Menart, and J. Miller. "Blunt Body in Hypersonic Electromagnetic Flow Field." Journal of Aircraft 40, no. 2 (March 2003): 314–22. http://dx.doi.org/10.2514/2.3095.

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6

Carlson, Henry A. "Aerothermodynamic Analyses of Hypersonic, Blunt-Body Flows." Journal of Spacecraft and Rockets 36, no. 6 (November 1999): 912–15. http://dx.doi.org/10.2514/2.3511.

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7

Knops, R. J., and Piero Villaggio. "An Approximate Treatment of Blunt Body Impact." Journal of Elasticity 72, no. 1-3 (2003): 213–28. http://dx.doi.org/10.1023/b:elas.0000018776.92471.36.

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8

Dogra, Virendra K., James N. Moss, Richard G. Wilmoth, Jeff C. Taylor, and H. A. Hassan. "Blunt body rarefied wakes for Earth entry." Journal of Thermophysics and Heat Transfer 9, no. 3 (July 1995): 464–70. http://dx.doi.org/10.2514/3.688.

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9

Golovachev, Yu P., V. B. Zemlyakov, and E. V. Matvienko. "Supersonic swirling flow past a blunt body." Fluid Dynamics 29, no. 6 (November 1994): 869–71. http://dx.doi.org/10.1007/bf02040797.

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10

Ng, K. C. "Retention of an ingested small blunt foreign body." Journal of the Belgian Society of Radiology 94, no. 6 (June 7, 2011): 339. http://dx.doi.org/10.5334/jbr-btr.702.

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Дисертації з теми "Blunt body"

1

Dominy, Robert Gerald. "Rarefied hypersonic shock wave and blunt body flows." Thesis, Imperial College London, 1988. http://hdl.handle.net/10044/1/47034.

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2

Castledine, Andre J. "Investigation of the fluid flow around blunt body samplers." Thesis, University of Leeds, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305756.

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3

Ess, Peter. "Numerical simulation of blunt body-generated detonation wave ramjet flowfields." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape8/PQDD_0019/MQ45873.pdf.

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4

Jain, Sunny. "Hypersonic nonequilibrium flow simulations over a blunt body using bgk simulations." [College Station, Tex. : Texas A&M University, 2007. http://hdl.handle.net/1969.1/ETD-TAMU-2406.

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5

Ess, Peter. "Numerical simulation of blunt-body generated detonation waves in viscous hypersonic ducted flows." Thesis, University of Bristol, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.288263.

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6

Johnson, Joshua E. "Multidisciplinary optimization of non-spherical, blunt-body heat shields for a planetary entry vehicle." College Park, Md. : University of Maryland, 2006. http://hdl.handle.net/1903/3766.

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Анотація:
Thesis (M.S.) -- University of Maryland, College Park, 2006.
Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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7

Johnson, Joshua E. "Aerothermodynamic optimization of earth entry blunt body heat shields for lunar and Mars return." College Park, Md.: University of Maryland, 2009. http://hdl.handle.net/1903/9177.

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Thesis (Ph.D.) -- University of Maryland, College Park, 2009.
Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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8

Aubuchon, Vanessa V. "Damping Effects of Drogue Parachutes on Orion Crew Module Dynamics." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23327.

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Currently, simulation predictions of the Orion Crew Module (CM) dynamics with drogue parachutes deployed are under-predicting the amount of damping as seen in free-flight tests.  The Apollo Legacy Chute Damping model has been resurrected and applied to the Orion system.  The legacy model has been applied to predict CM damping under drogue parachutes for both Vertical Spin Tunnel free flights and the Pad Abort-1 flight test.  Comparisons between the legacy Apollo prediction method and test data are favorable.  A key hypothesis in the Apollo legacy drogue damping analysis is that the drogue parachutes\' net load vector aligns with the CM drogue attachment point velocity vector.  This assumption seems reasonable and produces good results, but has never been experimentally verified.  The wake of the CM influences the drogue parachutes, which makes performance predictions of the parachutes difficult.  Many of these effects are not currently modeled in the simulations.  

A forced oscillation test of the CM with parachutes was conducted in the NASA LaRC 20-Ft Vertical Spin Tunnel (VST) to gather additional data to validate and refine the Apollo legacy drogue model.  A second loads balance was added to the original Orion VST model to measure the drogue parachute loads independently of the CM.  The objective of the test was to identify the contribution of the drogues to CM damping and provide additional information to quantify wake effects and the interactions between the CM and parachutes.  The drogue parachute force vector was shown to be highly dependent on the CM wake characteristics.  Based on these wind tunnel test data, the Apollo Legacy Chute Damping model was determined to be a sufficient approximation of the parachute dynamics in relationship to the CM dynamics for preliminary entry vehicle system design.  More wake effects should be included to better model the system. These results are being used to improve simulation model fidelity of CM flight with drogues deployed, which has been identified by the project as key to a successful Orion Critical Design Review.
Master of Science
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9

Kurits, Inna. "Quantitative global heat-transfer measurements using temperaure-sensitive [sic] paint on a blunt body in hypersonic flows." College Park, Md. : University of Maryland, 2008. http://hdl.handle.net/1903/8302.

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Анотація:
Thesis (M.S.) -- University of Maryland, College Park, 2008.
Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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10

Pinn, Jarred Michael. "Effect of End-Plate Tabs on Drag Reduction of a 3D Bluff Body with a Blunt Base." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/698.

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Анотація:
This thesis involves the experimental testing of a bluff body with a blunt base to evaluate the effectiveness of end-plate tabs in reducing drag. The bluff body is fitted with interchangeable end plates; one plate is flush with the rest of the exterior and the other plate has small tabs protruding perpendicularly into the flow. The body is tested in the Cal Poly 3ft x 4ft low speed wind tunnel. Testing is conducted in three phases. The first phase was the hot-wire measurement of streamwise velocity of the near wake behind the bluff body. An IFA300 thermal anemometry system with a hot-wire probe placed behind the model measures the wake velocity fluctuations. The power spectral density on the model without tabs shows large spikes at Strouhal numbers of 0.266, 0.300, and 0.287 at corresponding Re = 41,400, 82,800, 124,200 where vortex shedding occurs. The model with tabs shows no such peaks in power and therefore has attenuated vortex generation in the wake flow at that location. The second phase of testing was pressure testing the model through the use of pressure ports on the exterior of the bluff body. A Scanivalve pressure transducer measured multiple ports almost simultaneously through tubing that was connected to the model internally and routed through the model’s strut mount and outside of the wind tunnel. This pressure testing shows that the model with tabs is able to achieve up to 36% increase in Cp at Reh = 41,400 on the base region of the bluff body and no negative pressure spikes that occur as a result of vortex shedding. The last phase of testing is the measurement of total drag on the model through a sting balance mount. This testing shows that the drag on the model is reduced by 14% at Re = 41,400. However it also shows that as velocity increased, the drag reduction is reduced and ultimately negated at Re = 124,200 with no drag loss at all. The addition of tabs as a passive flow control device did eliminate vortex shedding and alter the base pressure of the bluff body. This particular model however showed no reduction in total drag on the model at high Reynolds numbers higher than 124,000. Further study is necessary to isolate the exact geometry and flow velocities that should be able to produce more favorable drag results for a bluff body with this type of passive flow control device.
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Книги з теми "Blunt body"

1

Dunnett, Sarah Jane, and Derek Binns Ingham. The Mathematics of Blunt Body Sampling. Berlin, Heidelberg: Springer Berlin Heidelberg, 1988. http://dx.doi.org/10.1007/978-3-642-83563-6.

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2

Dunnett, S. J. The mathematics of blunt body sampling. Berlin: Springer-Verlag, 1988.

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3

K, Dogra V., and United States. National Aeronautics and Space Administration., eds. Effects of chemistry on blunt-body wake structure. Washington, DC: American Institute of Aeronautics and Astronautics, 1995.

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4

L, Montagne J., and Ames Research Center, eds. Hypersonic blunt body computations including real gas effects. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

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5

K, Dogra V., and United States. National Aeronautics and Space Administration., eds. Effects of chemistry on blunt-body wake structure. Washington, DC: American Institute of Aeronautics and Astronautics, 1995.

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6

Institute for Computer Applications in Science and Engineering., ed. Spectral solution of the viscous blunt body problem. Hampton, VA: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1994.

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7

L, Montagne J., and Ames Research Center, eds. Hypersonic blunt body computations including real gas effects. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

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8

Ess, Peter. Numerical simulation of blunt body generated detonation wave ramjet flowfields. Ottawa: National Library of Canada, 1999.

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9

M, Price J., and United States. National Aeronautics and Space Administration., eds. Review of blunt body wake flows at hypersonic low density conditions. Washington, D.C: American Institute of Aeronautics and Astronautics, 1996.

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10

Kopriva, David A. Spectral solution of the viscous blunt body problem. II: Multidomain approximation. Hampton, Va: Langley Research Center, 1994.

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Частини книг з теми "Blunt body"

1

Mölder, Sannu. "Blunt Body Flow — The Transonic Region." In Shock Waves @ Marseille I, 101–4. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-78829-1_15.

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2

Schall, E., and D. Zeitoun. "Nonequilibrium Hypersonic Flow Around a Blunt Body." In Shock Waves @ Marseille II, 321–26. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-78832-1_53.

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3

Montagné, J. L., H. C. Yee, G. H. Klopfer, and M. Vinokur. "Hypersonic Blunt Body Computations Including Real Gas Effects." In Nonlinear Hyperbolic Equations — Theory, Computation Methods, and Applications, 413–22. Wiesbaden: Vieweg+Teubner Verlag, 1989. http://dx.doi.org/10.1007/978-3-322-87869-4_42.

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4

Fey, Michael, Rolf Jeltsch, and Peter Karmann. "Special aspects of reacting inviscid blunt body flow." In Hypersonic Flows for Reentry Problems, 664–76. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_55.

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5

Délery, Jean. "Separation Induced by an Obstacle or a Blunt Body." In Three-dimensional Separated Flow Topology, 91–120. Hoboken, NJ USA: John Wiley & Sons, Inc., 2013. http://dx.doi.org/10.1002/9781118578544.ch5.

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6

Reshotko, Eli, and Anatoli Tumin. "The Blunt Body Paradox — A Case for Transient Growth." In Laminar-Turbulent Transition, 403–8. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_60.

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7

Shi, Jiatong, Ketian Shi, and Liang Zhang. "Uniform Aero-Heating Flux Design for a Hypersonic Blunt Body." In Lecture Notes in Electrical Engineering, 335–45. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_27.

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8

Ohnishi, N., Y. Inabe, K. Ozawa, and K. Ohtani. "Critical Condition of Bow-Shock Instability Around Edged Blunt Body." In 31st International Symposium on Shock Waves 2, 1087–93. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_135.

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9

Smith, F. T. "Theory of High-Reynolds-Number Flow Past a Blunt Body." In Studies of Vortex Dominated Flows, 87–107. New York, NY: Springer New York, 1987. http://dx.doi.org/10.1007/978-1-4612-4678-7_7.

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10

Satheesh, K., and G. Jagadeesh. "Effect of electric arc discharge on hypersonic blunt body drag." In Shock Waves, 577–82. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85168-4_92.

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Тези доповідей конференцій з теми "Blunt body"

1

PEERY, K., and S. IMLAY. "Blunt-body flow simulations." In 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2904.

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2

Vaganov, A. V., A. Yu Noev, V. N. Radchenko, and A. G. Zdor. "INVESTIGATION OF BLUNT-BODY PARADOX." In INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH. Novosibirsk: Издательство Сибирского отделения РАН, 2022. http://dx.doi.org/10.53954/9785604788974_165.

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3

PEERY, K., S. IMLAY, and J. KATSANDRES. "Real-gas blunt-body flow simulations." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2179.

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4

Shang, J., J. Hayes, J. Miller, and J. Menart. "Blunt body in hypersonic electromagnetic flow field." In 32nd AIAA Plasmadynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-2803.

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5

Oliveira, Maria, and Chaoqun Liu. "Implicit LES for Shock/Blunt Body Interaction." 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/10.2514/6.2010-874.

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6

Poggie, J., and D. Gaitonde. "Magnetic control of hypersonic blunt body flow." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-452.

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7

Dwivedi, Anubhav, and Mihailo R. Jovanovic. "Noise amplification in hypersonic blunt body flows." In AIAA AVIATION 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-3709.

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8

STALKER, R. "A similarity transformation for blunt body flows." In 24th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-125.

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9

Rosema, Christopher, and David Riddle. "Aerodynamic Assessment of Several Blunt Body Configurations." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-910.

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10

Alhussan, Khaled. "Multi-Fins Decelerator for Blunt Body in Turbulent Flows." In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37460.

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The aim of this research is to use the numerical analysis techniques to design deceleration devices for a blunt body. In this paper a qualitative analysis of the flow structure over a blunt body with and without multi-fins decelerator was shown. In some applications of aerodynamics, a deceleration of a moving body is required therefore the prediction and controlling of the drag is essential. The deceleration devices such as air bag or fins can be added to the body to increase the aerodynamics drag. For a supersonic speed, a flow around blunt body is complicated due to the detached shock wave, flow separation, boundary layer and their interactions. When a decelerator is integrated with the blunt body the flow is subject to sever change of aerodynamic forces and velocity. The results will show that adding a deceleration device will change the flow structure behind the body especially with regard to the pressure drag and wake. Results of contour plots of Mach number and static pressure for zero angles of attack will demonstrate that the aerodynamic forces and the velocity are changed when the deceleration device is integrated with the blunt body. A number of important conclusions follow from the current research. First, study of the actual flow configuration over a blunt body with a decelerator offers some insight into the complex flow phenomena. Second, adding the decelerator will increase the separation that will result in an increase of total drag.
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Звіти організацій з теми "Blunt body"

1

Candler, Graham V. Effect of Internal Energy Excitation on Supersonic Blunt-Body Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, March 2001. http://dx.doi.org/10.21236/ada387503.

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2

Taylor, Paul A., and Candice Frances Cooper. Simulation of Blast and Behind-Armor Blunt Trauma to Life-Critical Organs in the Human Body. Office of Scientific and Technical Information (OSTI), September 2016. http://dx.doi.org/10.2172/1562207.

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Також вас можуть зацікавити розширені добірки на тему "Blunt body" для конкретних типів джерел:
Статті в журналах Дисертації Книги
Ми пропонуємо знижки на всі преміум-плани для авторів, чиї праці увійшли до тематичних добірок літератури. Зв'яжіться з нами, щоб отримати унікальний промокод!

До бібліографії