3 edition of Transpiration cooling in hypersonic flight found in the catalog.
Transpiration cooling in hypersonic flight
by National Aeronautics and Space Administration, Ames Research Center, For sale by the National Technical Information Service in Moffett Field, Calif, [Springfield, Va
Written in English
|Statement||Domingo Tavelia and Leonard Roberts.|
|Series||JIAA TR -- 92., NASA CR -- 186435., NASA contractor report -- NASA CR-186435.|
|Contributions||Roberts, L., Ames Research Center., Stanford University. Dept. of Aeronautics and Astronautics., Joint Institute for Aeronautics and Acoustics.|
|The Physical Object|
Gulli, L. Maddalena, and S. Hosder, “ Investigation of transpiration cooling effectiveness for air-breathing hypersonic vehicles,” in 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA, ), p. Details. The School of Metallurgy and Materials, in collaboration with the High Temperature Research Centre (HTRC) is seeking to recruit a PhD student as part of a multi-discipline EPSRC project on Transpiration Cooling Systems for Jet Engine Turbines and Hypersonic Flight.
Octra ‐ Optimized Ceramic for Hypersonic Application with Transpiration Cooling. Christian Dittert. The presented development is of fundamental importance for the realization of hypersonic vehicles, since the requirements for these applications are, among others, high temperature‐ and thermal shock resistance, low thermal expansion and Cited by: 2. Transpiration cooling is a thermodynamic process where cooling is achieved by a process of moving a liquid or a gas through the wall of a structure to absorb some portion of the heat energy from the structure while simultaneously actively reducing the convective and radiative heat flux coming into the structure from the surrounding space.
Transpiration cooling could be a means to handle the thermal loads in certain critical locations for a hypersonic flight vehicle. This paper describes the loads derived for a conceptual space plane vehicle, the SpaceLiner, and also reports on the initial tests for transpiration cooling of ceramic matrix composites in the hypersonic flow of an Cited by: Boehrk - - Transpiration Cooling at Hypersonic Flight - ( kB - downloaded times.) «Last Edit: 01/28/ pm by vaporcobra» Logged.
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The concept of transpiration cooling consists in allowing a gas- air, or, preferably a lighter gas such as helium - to transpire through porosity in the vehicle's skin.
Transpiration cooling could be a means to handle the thermal loads in certain critical locations for a hypersonic flight vehicle. This paper describes the loads derived for a conceptual space plane vehicle, the SpaceLiner, and also reports on the initial tests for transpiration cooling of ceramic matrix composites in the hypersonic flow of an arcFile Size: KB.
The present paper presents the in-flight measurement of the transpiration cooling experiment Aktive Kühlung durch Transpiration im Versuch (often referred to as AKTiV) flown on the suborbital reentry configuration Sharp Edge Flight Experiment II (often referred to as SHEFEX II).Cited by: Electron transpiration cooling (ETC) complements radiative cooling from the surface to balance with the convective heating from the flow.
This work focuses implementing ETC into the CFD code LeMANS to investigate the challenges and benefits it can provide to hypersonic flight including the effect of ETC on: surface temperature ; surface heating. Cerminara, Adriano, Deiterding, Ralf and Sandham, Neil () Transpiration cooling using porous material for hypersonic applications.
In, Mahmoudi, Yasser, Hooman, Kamel and Vafai, Kambiz (eds.) Convective Heat Transfer in Porous : Adriano Cerminara, Ralf Deiterding, Neil Sandham. Böhrk, Hannah Transpiration cooling in hypersonic flight book Transpiration Cooling at Hypersonic Flight - AKTiV on SHEFEXII.
11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, JuniAtlanta, USA. Dieses Archiv kann nicht den gesamten Text zur Verfügung by: HYPERSONIC AEROSPACE VEHICLE LEADING EDGE COOLING USING HEAT PIPE, TRANSPIRATION AND FLM COOLING TECHNIQUES OTIC ' J D 7 V ',L A THESIS i*0*30Tor Presented to i 1.
The Academic Faculty DT i by '. James Michael Modlin._-'.* " '- I., I In Partial Fulfillment of the Requirements for the DegreeCited by: 3. Transpiration cooling has been recognized the most effective cooling technology. This paper presents an experimental investigation on transpiration cooling using liquid water as coolant for a nose cone model of hypersonic vehicles.
The nose cone model consists of sintered porous material. The vehicle performs its rocket powered, intercontinental flight via a suborbital trajectory. The major challenge is the aerodynamic heating of the vehicle. This is discussed, and a possible solution for handling the extreme heatloads will be presented.
The solution involves an innovative new way of transpiration cooling, using liquid : A. van Foreest, M. Sippel, A. Gülhan, B. Esser. Transpiration Cooling Systems for Jet Engine Turbines and Hypersonic Flight Pismo Admin T+ The £ Million UK-EPSRC and Rolls Royce funded Transpiration Cooling project is a joint initiative between the University of Oxford, Imperial University, University of Southampton and the University of Birmingham.
Get this from a library. Transpiration cooling in hypersonic flight. [D A Tavella; L Roberts; Ames Research Center.; Stanford University.
Department of Aeronautics and Astronautics.; Joint Institute for Aeronautics and Acoustics.]. The highest temperatures achievable for both jet engines and hypersonic flight are limited by the materials and cooling technology used. The cooling benefits of transpiration flows are well established, but the application of this technology to aerospace in the UK has been prevented by the lack of suitable porous materials and the challenge of accurately modelling.
Thus, cooling is needed to protect hypersonic vehicles during long flights. Transpiration cooling is an effective way to cool high heat flux surfaces .  Brune A., Hosder S., Gulli S. and Maddalena L., “ Numerical Investigation of Transpiration Cooling Effectiveness in Laminar and Turbulent Flows for Hypersonic Cruise Vehicles,” 51st AIAA Aerospace Sciences Meeting, AIAA PaperJan.
Cited by: 3rd International Symposium on Hypersonic Flight Air Force Academy (Pozzuoli), Italy, May ESA UNCLASSIFIED - For Official Use FLIGHT VEHICLES AND AEROTHERMODYNAMICS ENGINEERING.
Transpiration Cooling ic TD • 5 year programme, focussed on development of fundamental. Böhrk, Hannah () Transpiration-Cooled Hypersonic Flight Experiment: Setup, Flight Measurement, and Reconstruction.
Journal of Spacecraft and Rockets, 52 (3), Seiten American Institute of Aeronautics and Astronautics (AIAA). DOI: /1.A ISSN Dieses Archiv kann nicht den gesamten Text zur Verfügung by: When the intensity of the shock wave further increases (θ = 10°), the boundary layer even separates and results in a fluid backflow in the boundary layer.
More coolant flows to the upstream region because of the non-uniform static pressure distribution, and the transpiration cooling efficiency is thus by: 6.
Transpiration and Effusion Cooling Methods for Hypersonic Vehicles This project deals with an active cooling system for hypersonic vehicles and should prove the effectiveness of such a system. A high effectiveness lowers the structural weight of the thermal protection system and increases its reliability.
This article reports the results of applying a finite-difference-based computational technique to the problem of predicting the transient thermal behavior of a scramjet engine inlet exposed to a typical hypersonic flight aerodynamic surface heating environment, including type IV shock interference heating.
The leading-edge cooling model utilized incorporates liquid metal heat pipe cooling Cited by: Transpiration cooling applied to modern ceramic matrix composite materials is an interesting concept for thermal protection of future aerospace applications.
Therefore, reliable and accurate numerical tools for the simulation of transpiration cooling processes in complex flow situations and for complex porous geometries are needed. In this study, we present a fully Author: Daniel Prokein, Christian Dittert, Hannah Böhrk, Jens von Wolfersdorf.
Transpiration Cooling at Hypersonic Flight - AKTiV on SHEFEXII. By Hannah Böhrk. Abstract. The present paper presents the in-flight measurement of the transpiration cooling experiment AKTiV flown on the sub-orbital re-entry configuration SHEFEXII.
Thermal\ud response of the structure is measured just up- and downstream of a cooled sample with Cited by: The results presented indicated that the combined opposing jet cooling and transpiration cooling had a significant influence on the flow filed.
In addition, their work highlighted that the combined opposing jet and transpiration cooling was more effective than pure transpiration cooling for cooling the strut.A Space Application: Hypersonic Flight Figure Transpiration-cooled Leading Edge as sketched by Bulman.
This chapter gives an overview of the application of novel permeable composites for the transpiration-cooling of space-related high-temperature structures.