Hot-jet simulation in cryogenic wind tunnels by Keisuke Asai

Cover of: Hot-jet simulation in cryogenic wind tunnels | Keisuke Asai

Published by National Aeronautics and SpaceAdministration in Washington D.C .

Written in English

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Edition Notes

At foot of title: National Aeronautics and Space Administration Scientific and Technical Information Division.

Book details

StatementKeisuke Asai.
SeriesNASA reference publication -- 1220
ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Division.
ID Numbers
Open LibraryOL13931490M

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It has been shown that cryogenic wind tunnel testing provides an opportunity for the most accurate hot- jet simulation. By using compressed nitrogen gas at ambient or moderately elevated temperatures as a jet gas, almost all the relevant similarity parameters, including the jet temperature and velocity ratiosFile Size: 1MB.

Hot-jet simulation in cryogenic wind tunnels. Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Keisuke Asai.

Experiments to evaluate hot-jet simulation capabilities in CryogenicWind-Tunnel testing. Interaction of two-dimensional hot jet and two two-dimensional cold jets.

A high speed wind tunnel test evaluation of STOL dedicated advanced exhaust nozzle concepts. It was shown that the cryogenic wind tunnel testing provides an opportunity for the most accurate hot jet simulation technique.

By using a compressed nitrogen gas at ambient or moderately elevated temperatures as a jet gas, most all of the relevant similarity parameters including the jet temperature and velocity ratios and the Reynolds numbers, can be set to the full scale flight : Keisuke Asai.

Therefore, the development of intermittent cryogenic wind tunnels seems to be necessary in the same way that many short duration wind tunnels have been developed for atmospheric temperatures. In this paper we report a flashing blowdown cryogenic wind tunnel developed at the Muroran Institute of Technology [MH(Maeno-Hanaoka)].Cited by: 1.

Hot jets-in-cross-flow are frequently encountered in aeronautics and the accurate estimation of the wall temperature in the jet wake is crucial during the early design of a new aircraft.

However, common two-equation RANS models fail at estimating Hot-jet simulation in cryogenic wind tunnels book wall temperature in the jet by: 2. Simulation and Modeling of Jet Plumes in Wind Tunnel Facilities.

The wind tunnel simulation of propulsion jets and their modeling by congruent plumes including limits of Cited by: 5. Three-Dimensional Simulation of Turbulent Hot-Jet Ignition for Air-CH4-H2 Deflagration in a Confined Volume Article in Flow Turbulence and Combustion (4).

“European Strategic Wind tunnels Improved Research Potential” ESWIRP is a project in the EU 7th Framework program (FP7), which was aiming at improving the performance capabilities of three strategic wind tunnels in Europe, by strengthening the cooperation between these wind tunnels in a new Size: 1MB.

The Cryogenic Wind Tunnel Cologne (KKK) is a closed circuit low speed tunnel (Fig. To achieve high Reynolds-numbers, the gas temperature in the tunnel circuit can be lowered down to K by injecting liquid nitrogen.

The Reynolds number can be thus increased by a factor of while the drive power and Mach numberCited by: 2. Abstract. This paper opens with a brief review of cryogenic wind tunnels and their use for high Reynolds number testing.

Emphasis is on operational and aerodynamic testing experience in the NASA Langley m Transonic Cryogenic Tunnel (TCT).Cited by: 6.

temperature range given in cryogenic wind tunnel testing ( K TSP paint for cryogenic wind tunnel testing ‘only’ covered the temperature range File Size: KB.

Instead, a pure nitrogen flow with a temperature down to Kelvin (= °C = °F) is driven through the closed aerodynamic circuit of the wind tunnel, subjected to pressures up to bars and passes through the test section at speeds up to the low supersonic range (M = ).

CFD methods and cryogenic wind tunnel testing are typically being incorporated early in the process when designing a modern transonic transport. The currently developed Boeing was tested in the ETW early on in Hot-jet simulation in cryogenic wind tunnels book design process and the final determination of how well the wind tunnel data matches flight performance will follow from.

This wind tunnel will be used for educational and research purposes. It will have a high quality flow, up to 50 m/s, in a test section of 1,4 x 1,0 x 2,0 m 3. It will be used for typical aerodynamic tests and airfoil cascade tests (utilising the first corner of the wind tunnel circuit).Cited by: Get this from a library.

Hot-jet simulation in cryogenic wind tunnels. [Keisuke Asai; United States. National Aeronautics and Space Administration. Scientific. The purpose of this paper is to review the theory and some of the advantages of the cryogenic wind tunnel concept and to describe briefly some of the features of the NTF that relate more directly to cryogenic engineering.

THE CRYOGENIC CONCEPT The idea of cooling the test gas in order to increase the Reynolds number capability of a wind Cited by:   The development of the cryogenic wind tunnel is one of many significant breakthroughs in both cryogenics and wind-tunnel technology made during the past millennium.

Interest in the development of high-speed commercial and military aircraft resulted in a review of problems of flow simulation in transonic wind tunnels during the s and 60s. Together with the K-Site facility, these facilities compose the Cryogenic Test Complex.

+ View site: Hypersonic Tunnel Facility (HTF) A unique wind tunnel designed to test air-breathing propulsion systems at speeds exceeding 5 times the speed of sound. + View site.

The velocity of the hot jet was specified as 15 m/s and that of the main flow as 19 m/s to counteract the change in velocity due to temperature effects. Turbulent intensity was set as 1%. Spalart-Allmaras model was used, and air was considered to be an ideal gas.

The temperature of the hot jet inlet was varied between the K and : Merlin C. Das, Meribeni L. Jungio, N. Haritha, Abhilash Suryan, Heuy Dong Kim. Cryogenic wind tunnel is a sophisticated aerodynamics ground test facility, which operates in cryogenic temperature with injection of liquid nitrogen.

The multi-variable, nonlinear and coupled dynamics existing between the temperature, pressure and Mach number in the tunnel, poses great challenges for the effective control of the tunnel.

L1 adaptive control is a new control. Inwork was started on the conversion of a subsonic wind tunnel to a foot transonic tunnel with Freon or air as the test medium. The new facility, designated the.

For wind tunnel testing of aircraft, scientists and engineers mount a model of the aircraft in the wind tunnel to maintain its position under varying forces, allowing a realistic simulation of. Full text of "Model Deformation Measurements at a Cryogenic Wind Tunnel Using Photogrammetry" See other formats 1 iT MODEL DEFORMATION MEASUREMENTS AT A CRYOGENIC TUNNEL USING PHOTOGRAMMETRY X WIND I 1 I 1 t A.

Burner, W. Snow, W. Goad NASA iLangley Research Center Hampton, VA »• ABSTRACT A. nasa technical note nasa tn d ini-(nasa-tn-d) the cryogenic wind n tunnel concept for high reynolds number testing (nasa) 96 p hc $ cscl 14b unclas h the cryogenic wind-tunnel concept for high reynolds number testing by robert a.

kilgore, michael j. Wind tunnel tests in a boundary layer wind tunnel allow for the natural drag of the Earth's surface to be simulated. For accuracy, it is important to simulate the mean wind speed profile and turbulence effects within the atmospheric boundary layer.

Turn your device into a wind tunnel simulator. Draw obstacles and watch the fluid flow around. Experiment with different sizes, shapes, aerodynamic profiles and see what happens. Visualize airflow with smoke, particles, or observe pressure field, velocity.

The simulation engine also computes an approximation of lift and drag. The Wind Tunnel free app lets you play with the /5(K). Modeling and control study of the NASA meter transonic cryogenic tunnel for use with sulfur hexafluoride medium - Kindle edition by NASA, National Aeronautics and Space Administration.

Download it once and read it on your Kindle device, PC, phones or tablets. Use features like bookmarks, note taking and highlighting while reading Modeling and control study of the NASA Author: National Aeronautics and Space Administration NASA.

installed in a high-speed cryogenic wind tunnel facility for use at free stream Mach numbers between and and pressures between and bar. The necessary particle seeding was achieved by injecting a mixture of gaseous nitrogen and water vapor into the dry and cold tunnel flow which then immediately formed a large.

Hot-jet simulation in cryogenic wind tunnels [] Asai, Keisuke. Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, Six component full or half model balances (also for cryogenic applications) Wind tunnel parts and instrumentation; NLR can help you get the most out of your test by designing, manufacturing and instrumenting specialized wind tunnel equipment.

NLR can assist you from the early beginning of the project until the commissioning and beyond. The schematic of wind tunnel structures presented in Figures 1, 2, and 3 gives only a general idea of the variety of operational regimes of wind tunnels.

Thus, bottles, exhaust fans, and vacuum vessels are used, as a rule, in open-circuit wind tunnels designed for gas ejection and single gas utilization in the working section (Figure 2). Abstract: The determination of the transonic position on a two dimensional model is an important subject of studies in the ONERA-CERT T2 cryogenic wind tunnel.

The use of liquid crystals with a specific methodology of calibration, acquisition and image processing allowed one to go beyond the usual stage of qualitative imaging and to determine the temperature map on the surface of.

The real gas behavior of nitrogen, the gas normally used in transonic cryogenic tunnels, is reported for the following flow processes: isentropic expansion. This book presents current research in the study of wind tunnels, including the design, execution and numerical rebuilding of a plasma wind tunnel with the aim to analyse shock wave boundary layer interaction phenomena; the Mainz vertical wind tunnel facility experimenting on cloud physics and chemistry; an air-conditioned wind tunnel environment for the study of mass and heat flux; using wind Cited by: 8.

Pharmaceutical Chemistry. Heteroresistance: a concern of increasing clinical significance. Textbook of human genetics. Pure and Applied Mathematics.

Organic spectroscopy. Oxford Handbook of Paediatrics (Oxford Medical Handbooks) Oral Anatomy, Histology and Embryology. Textbook of Medical-Surgical Nursing. Textbook of Human Embryology. The Cologne Cryogenic Wind Tunnel (KKK) is instrumented with internal balances. There has been high demand from the tunnel customers to make half model tes Half-model-balance for the Cologne-cryogenic-wind-tunnel development and test results - IEEE Conference PublicationCited by: 3.

True simulation of full scale transonic Reynolds numbers did not become possible until a complete break was made with conventional wind tunnel design inwhen the NASA meter transonic cryogenic tunnel went on line at Langley.

It was cost that deterred the construction of full scale conventional wind tunnels in the transonic regime. The only way to get both Reynolds and Mach number similarity for models (unless you change the medium) is to use pressurized and/or cryogenic wind tunnel.

The cryogenic wind tunnel achieves the required Reynolds number by reducing the viscous forces rather than increasing the inertial forces; even then the actual Reynolds numbers encountered in.

The Langley 8-Foot High Temperature Tunnel (8-Ft HTT) is a combustion-heated hypersonic blowdown-to-atmosphere wind tunnel that provides simulation of flight enthalpy (relationship of an object, its environment, and energy) for Mach numbers of 4, 5, and 7 and Reynolds numbers from x 10 6 to x 10 6 per foot, depending on the Mach number.

A Computational Fluid Dynamic Study for Temperature Uniformity at a Wind Tunnel Outlet with Effects of Heat Transfer along Tunnel Walls. Li Song 1,2, Chen XiaoBing 3, Huang ZhiLong 1,2 and Liao DaXiong 1.

Published under licence by IOP Publishing Ltd IOP Conference Series: Materials Science and Engineering, Volumeconference 1Author: Li Song, Chen XiaoBing, Huang ZhiLong, Liao DaXiong.Iijima Y, Egami Y, Nishizawa A, Asai K, Fey U and Engler R H Optimization of temperature-sensitive paint formulation for large-scale cryogenic wind tunnels Proc.

20th Int. Congress on Instrumentation in Aerospace Simulation Facilities (ICIASF), Record (Goettingen, Germany,) pp 70–6. Google Scholar.Purdue University - School of Aeronautics and Astronautics. AAE Experimental Aerodynamics Wind Tunnels Objective Accurately simulate the fluid flow about atmospheric vehicles Measure -Forces, moments, pressure, shear stress, heat transfer, flowfield (velocity, pressure, vorticity, temperature) Purdue University - School of Aeronautics and Astronautics .

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