Experimental results for a hypersonic nozzle/afterbody flow field

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National Aeronautics and Space Administration, Ames Research Center, National Technical Information Service, distributor , Moffett Field, Calif, [Springfield, Va
StatementFrank W. Spaid, Earl R. Keener, Frank C.L. Hui.
SeriesNASA technical memorandum -- 4638.
ContributionsKeener, Earl R., Hui, Frank C. L., Ames Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL16984453M
OCLC/WorldCa32851606

Get this from a library. Experimental results for a hypersonic nozzle/afterbody flow field. [Frank W Spaid; Earl R Keener; Frank C L Hui; Ames Research Center.]. EXPERIMENTAL RESULTS FOR A HYPERSONIC NOZZLE/AFTERBODY FLOW FIELD Frank W. Spaid,* Earl R.

Keener, t and Frank C. Hui Ames Research Center SUMMARY This study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion-ramp-nozzle (SERN) flow with a hyper-sonic external stream. Gruhn P., Henckels A.

() Simulation of a SERN/Afterbody Flow Field Regarding Heated Nozzle Flow in the Hypersonic Facility H2K. In: Breitsamter C., Laschka B., Heinemann Experimental results for a hypersonic nozzle/afterbody flow field book, Hilbig R.

(eds) New Results in Numerical and Experimental Fluid Mechanics IV. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol Cited by: 1. A nozzle shape optimization study for a quasi-axisymmetric scramjet has been performed for a Mach operating condition with hydrogen fuel, aiming at the application of a hypersonic airbreathing vehicle.

In this study, the nozzle geometry which is parameterized by a set of design variables, is optimized for the single objective of maximum net thrust using an in Cited by: 4.

Using an implicit Finite-Volume Navier-Stokes code the flow field in a Single Expansion Ramp Nozzle (SERN) for a hypersonic aircraft is studied.

Comparisons between experimental data and CFD calculations for certain components of the integrated exhaust system (cold 2D nozzle flow, high temperature reacting 3D combustion chamber flow and 2D Author: Thomas Esch, Marcus Glehrl.

The flow field created by the interaction of a single-expansion-ramp-nozzle (SERN) flow with a hypersonic external stream has been experimentally characterized using a generic nozzle/afterbody.

Arc-heated gas flow experiments for hypersonic propulsion applications of a generic 2-D hypersonic nozzle/afterbody configuration was studied experimentally. in the midst of boundary layer.

Hypersonic Nozzle-Afterbody Experiment: Flow Visualization and Boundary-Layer Measure-ments A Hypersonic Nozzle-Afterbody Experiment: Flow-field Surveys A Experimental Investigation of Side-Jet Steering for Supersonic and Hypersonic Missiles A Experimental and Numerical Study of Hyperson-ic Forward-Facing Cavity Flow A The main objectives of the study were: (1) to identify the interactions between the two exhaust jet streams during the transition mode phase and their effects on the whole flow-field structure; (2) to determine and verify the aerodynamic performance of the over–under TBCC exhaust nozzle; and (3) to validate the simulation ability of the Cited by: 9.

Abstract. Various papers on numerical methods for engine-airframe integration are presented. The individual topics considered include: scientific computing environment for the s, overview of prediction of complex turbulent flows, numerical solutions of the compressible Navier-Stokes equations, elements of computational engine/airframe integrations, computational.

@article{osti_, title = {Tactical missile aerodynamics - Prediction methodology. Progress in Astronautics and Aeronautics. Vol. }, author = {Mendenhall, M.R.}, abstractNote = {The present volume discusses tactical missile aerodynamic drag, drag-prediction methods for axisymmetric missile bodies, an aerodynamic heating analysis for supersonic missiles, a.

Flight-measured effects of boattail angle and Mach number on the nozzle afterbody flow of a twin-jet fighter.

The flow field about and forces on slender bodies at high angles of attack. Experimental results of the solar heating system on the LSU field house.

MAPLES. This book contains chapters written by some eminent scientists and researchers on Computational Methods in Hypersonic Aerodynamics and forms a natural sequel to the earlier publications on Computational Methods in Potential Flow () and Computational Methods in Viscous Aerodynamics ().

In this book basics of aerothermodynamics are treated, which are of importance for the aerodynamic and structure layout of hypersonic flight vehicles. It appears to be useful to identify from the beginning classes of hy­personic vehicles, because aerothermodynamic phenomena can have different importance for different vehicle classes.

The Defense Technical Information Center (DTIC) is the premier repository for research and engineering information for the United States Department of Defense.

DTIC's Suite of Services is available to DoD personnel, defense contractors, federal. This volume - the third and final in a mini-series on hypersonic propulsion along with High Speed Flight Propulsion Systems, volumeand Developments in High Speed Flight Propulsion Systems, volume - presents a comprehensive and detailed exposition of the gradual maturing of scramjet technologies.

In this paper critical review of the literature is carried out and a conceptual design of short takeoff supersonic aircraft with cold flow multi-purpose rectangular nozzle has been proposed.

Download Experimental results for a hypersonic nozzle/afterbody flow field EPUB

Bachelor of Engineering Final Year Student, Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore –Tamil Nadu. A theory for base pressures in transonic and supersonic flow / (Urbana, Ill.: Mechanical Engineering Dept., Univ.

of Illinois, May ), by Helmut Hans Korst, M. Childs, R. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only).

Experimental investigation of the mixing loss behind trailing edge of a cascade of three 90© supersonic turning passages / (Washington, D.C.: National Advisory Committee for Aeronautics, ), by Luke L.

Details Experimental results for a hypersonic nozzle/afterbody flow field EPUB

Liccini, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. Full text of "DTIC ADA Aerodynamic Engine/Airframe Integration for High Performance Aircraft and Missiles (L'Integration Aerodynamique des Moteurs et des Cellules dans les Avions et les Missiles a Hautes Performances)" See other formats.

The basics of aerothermodynamics are treated in this book with special regard to the fact that outer surfaces of hypersonic vehicles primarily are radiation cooled. The implications of this fact are different for different vehicle classes.

Description Experimental results for a hypersonic nozzle/afterbody flow field EPUB

In any case the properties of both attached viscous and separated flows are of importance in this regard. Conceptual Design of Short Takeoff Supersonic Aircraft with Cold Flow Nozzles Vignesh.

M 1, Sathish. K1, Adrin Issai Arasu. L1, Dharun Lingam. K1, and Sanal Kumar. V.R 2 consumption and poor range) in turn making it unprofitable for manufacturers to produce these kinds of aircraft.

It can cover a distance from India to USA in 2 ½ hours. Dan M. Somers, Design and Experimental Results for a Flapped Natural-Laminar-Flow Airfoil for General Aviation Applications, NASA TP, Junepp.

Charlie M. Jackson, Jr., William A. Corlett and William J. Monta, Description and Calibration of the Langley Unitary Plan Wind Tunnel, NASA TP, Novemberpp. The department has a laboratory with several permanent experimental facilities and advanced measurement equipment.

A major experimental facility is the MTL wind-tunnel, which is a low-turbulence wind-tunnel with outstanding flow quality. It has a 7 m long ( m x m) test section and a maximum speed of 69 m/s. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.

Airbreathing hypersonic flight vehicles are, in contrast to aeroassisted re-entry vehicles, drag sensitive. They have, further, highly integrated lift and propulsion systems. This means that viscous eflFects, like boundary-layer development, laminar-turbulent transition, to a certain degree also strong interaction phenomena, are much more.

fd and applications. Experimental results for a hypersonic nozzle/afterbody flow field. NASA Technical Reports Server (NTRS) Spaid, Frank W.; Keener, Earl R.; Hui, Frank C. This study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion ramp-nozzle (SERN) flow with a hypersonic external stream.

Full text of "NASA Technical Reports Server (NTRS) A cumulative index to Aeronautical Engineering: A continuing bibliography, supplement " See other formats.

AGARD-R[1] Published on July AGARD AR/FDP WG0 Testcases for inviscid flow field methods ACARD AR/FDP WG 08 Aerodynamics of aircraft afterbody International vortex flow experiment on Euler code validation FFA Stockholm AGARD CP CFD validation computations If no viscous results on similar use of experimental wing.

Experimental results for a hypersonic nozzle/afterbody flow field. NASA Technical Reports Server (NTRS) Spaid, Frank W.; Keener, Earl R.; Hui, Frank C.

L. This study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion ramp-nozzle (SERN) flow with a hypersonic external stream.

Data were obtained from a generic nozzle/afterbody.hypersonic flow past the radiation-cooled surface of a generic configuration (Blunt Delta Wing (BDW) [34]). The configuration is a simple slender delta wing with blunt nose. Fig. Navier-Stokes solutions for perfect gas were performed for fiight with the conditions given in Table Laminar flow was assumed.oil-free turbomachinery technology for regional jet, computational and experimental investigation of flow in counter rotating propfans including reverse thrust regimes.

oil-free turbomachinery technology for regional jet, rotorcraft and .