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Saturday, April 25, 2020 | History

3 edition of Research on a two-dimensional inlet for a supersonic V/STOL propulsion system found in the catalog.

Research on a two-dimensional inlet for a supersonic V/STOL propulsion system

Research on a two-dimensional inlet for a supersonic V/STOL propulsion system

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  • 27 Currently reading

Published by McDonnell Aircraft Company, McDonnell Douglas Corporation, National Aeronautics and Space Administration, Lewis Research Center in St. Louis, Mo.], [Cleveland, Ohio] .
Written in English

    Subjects:
  • Aircraft design.,
  • Design analysis.,
  • Inlet flow.,
  • Performance tests.,
  • V/STOL aircraft.

  • Edition Notes

    Other titlesResearch on a two dimensional inlet for a supersonic V/STOL propulsion system.
    Statementby J.L. Mark, M.A. McGarry, and P.V. Reagan.
    SeriesNASA-CR -- 174945., NASA contractor report -- NASA CR-174945.
    ContributionsMcGarry, M. A., Reagan, P. V., McDonnell Aircraft Company., Lewis Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL16138646M

    The EWR VJ was an experimental German jet fighter vertical takeoff/landing tiltjet aircraft. VJ stood for Versuchsjäger, (German for "Experimental Fighter"). The VJ was one of the first V/STOL designs to have the potential for eventual Mach 2 flight.. During the s, as various nations took an interest in developing VTOL-capable aircraft, the German Federal Government issued a Manufacturer: EWR. Answers will vary. Suggested answers are shown below: Use the Gas Turbine Parts section located in the Propulsion Index of the Beginner's Guide to Propulsion to match the correct letter from above with the listed part. Write the corresponding letter for each part in the space to the right of the word. Hypersonic Vehicle Propulsion System Control Model Development Roadmap and Activities [Thomas J. Stueber, Nasa Technical Reports Server (Ntrs), Et Al] on *FREE* shipping on qualifying offers. The NASA Fundamental Aeronautics Program Hypersonic project is directed towards fundamental research for two classes of hypersonic vehicles: highly reliable reusable launch systems (HRRLS) Cited by: 4.


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Research on a two-dimensional inlet for a supersonic V/STOL propulsion system Download PDF EPUB FB2

First the propulsion system can be moved futher rearward to a point where it integrates better with the aircraft. Secondly, this rearward move- ment of the propulsion system leads to more length for installing the inlet which in turn permits the use of a two dimensional inlet (as opposed to a shorter axisymnetric inlet) with its inherentlyFile Size: 4MB.

Get this from a library. Research on a Research on a two-dimensional inlet for a supersonic V/STOL propulsion system book inlet for a supersonic V/STOL propulsion system. [J L Mark; M A McGarry; P V Reagan; McDonnell Aircraft Company.; Lewis Research Center.].

Research on a two-dimensional inlet for a supersonic V/STOL propulsion system. Appendix A. By M. Mcgarry, P. Reagan and J. Mark. Abstract. The inlet system performance requirements associated with supersonic V/STOL aircraft place extreme demands on the inlet designer. The present effort makes maximum use of flow improvement techniques Author: M.

Mcgarry, P. Reagan and J. Mark. Three lift/propulsion concepts for a V/STOL supersonic combat aircraft Research on a two-dimensional inlet for a supersonic V/STOL propulsion system book been compared.

The intention was to show the effect of the propulsion system on aircraft weight and size, performance, and life cycle costs for:1Vectored thrust with Plenum Chamber Burning (bypass air augmentation)2Lift engiCited by: 3.

• The inlet flow field is divided into Parts that further helps establish parameters for defining the geometry. Example. A two-dimensional inlet shape for an external supersonic diffuser has ramps defined by Research on a two-dimensional inlet for a supersonic V/STOL propulsion system book.

Surface Grid Edges Edges • The Inlet Geometry Model consists of a patchwork of Surfaces. Mark has written: 'Research on a two-dimensional inlet for a supersonic V/STOL propulsion system' -- subject(s): Performance tests, Inlet flow, Aircraft design, V/STOL aircraft, Design analysis.

Nonlinear Dynamic Modeling and Controls Development for Supersonic Propulsion System Research. Two-Dimensional Bifurcated Inlet/Engine Tests Completed in 10 Research on a two-dimensional inlet for a supersonic V/STOL propulsion system book y N NASA Technical Memorandum 9 Supersonic STOVL Ejector Aircraft from a Propulsion Point of View R.

Luidens, R. Plencner, W. Haller, and A. blassman Lewis Research Center Cleveland, Ohio Prepared for the Twentieth Joint Propulsion Coiiference cosponsored by the AIAA, SAE, and ASME i Cincinnati, Ohio, JuneI.

A supersonic inlet has two parts. The supersonic diffuser for supersonic and the subsonic diffuser, it is long and heavy. The designer needs to know the size of the inlet in order to properly account for it during the conceptual and preliminary design stage. The designer also needs to estimate the total pressure recovery at the engine face in.

International Journal of Scientific and Research Publications, Volume 3, Issue 1, January 1 ISSN Design and Analysis on Scramjet Engine Inlet Aqheel Murtuza Siddiqui1, Ahmed2 1 Research Assistant, Muffakham Jah College of Engineering & Technology., HyderabadFile Size: 1MB.

We can find in this book a deep description the functions,operation about subsonic, supersonic diffuser, specially in missile application, the indispensable knowledge to whom involve in ramjet study.

The representation of this book is good combination between text, diagram and by: A wind tunnel test program was conducted to acquire flow-field data during a supersonic propulsion system compressor stall and inlet unstart sequence.

The propulsion system consisted of a mixed Author: A. Robert Porro. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Supersonic (Engine) Inlets • For air-breathing engines on supersonic vehicles, usually want to slow flow down to subsonic speeds inside engine – need diffuser (M>1→Minlet – exception: supersonic combustion (e.g., SCRAM jets) •Goal – lowest po loss (highest thrust) • given flight M • mass flow rate requirement (thrust)File Size: KB.

Having established this background the subject at hand, supersonic propulsion con-trol, can now be discussed. An inlet that might be used in a supersonic aircraft is shown in figure 3.

It is an axisymmetric, mixed-compression inlet with a translating centerbody. The inlet variables that a control would manipulate are called out in the Size: 6MB. a supersonic, two-dimensional, combination external-internal compression air inlet system havng a longitudinal axis and comprising: a first surface angled with respect to said axis and generating an initial oblique shock wave externally of the inlet, said first surface being selectively translatable fore and aft longitudinally of said inlet system; a forward floating surface generating at.

The primary motivation of this research is focused on reduced order modeling of supersonic inlets to be used as part of a larger propulsion system or aero-propulso-servo-elastic model. Investigation of Two-Dimensional Scramjet Inlet Flowfield at Mach 7 Article in Journal of Propulsion and Power 24() November with 90 Reads How we measure 'reads'.

J. Mark has written: 'Research on a two-dimensional inlet for a supersonic V/STOL propulsion system' -- subject(s): Performance tests, Inlet flow, Aircraft design, V/STOL.

A method has been developed to determine the location and strength of the terminal shock in the subsonic diffuser of a supersonic two-dimensional inlet, given the engine-face Mach number.

Research Center, General Electric has conducted Advanced Supersonic Propulsion System Technology Studies (AST). These studies have screened conventional and variable cycle concepts and combined features of both types into a variable cycle engine that has characteristics suited for sustained supersonic cruise.

Control-oriented models of hypersonic vehicle propulsion systems require a reduced-order model of the scramjet inlet that is accurate to within 10% but requires less than a few seconds of computational time.

To achieve this goal, a reduced-order model is presented, which predicts the solution of a steady two-dimensional supersonic flow.

This research details analysis completed towards extending scramjet operability to lower Mach numbers, while maintaining performance at higher Mach numbers within the same flowpath as detailed in the Air Force solicitation AFFile Size: 2MB.

USA USDA USA US A US A US A US D A USD A US DA US A US A US A Authority US United States Prior art keywords inlet air flow variable gap Prior art date Legal status (The legal status is an assumption and is not a legal conclusion.

Loss models used in compression system performance prediction codes are often developed from the study of two-dimensional cascades.

In this paper, compressible fluid mechanics has been applied to the changes in shock geometry that are known to occur with back pressure for unstarted operation of supersonic compressor by: 6.

Abstract. The results of designing and numerical gas-dynamic modeling a supersonic three-dimensional inlet of a new type are considered. A ramp of external compression of this inlet is the V-shaped body forming an initial plane oblique shock wave and a Cited by: 5.

Thruster, Detonation, Impulse, Supersonic Flow, Method of Characteristics, CFD, Nozzle 1. Introduction The increase thrust performance for a spaceplane and a rocke- t is important.

In particular, the development of high-efficiency propulsion is required in supersonic cruising. According to the background, a pulse detonation. The invention relates to aeronautical engineering and, more specifically, to air intakes for supersonic aircraft propulsion systems.

The technical result to be achieved by the invention consists in ensuring stable operation of the engine in all flight regimes up to the maximum Mach number of M= by adjusting the apex angle of stages of one of swept wedges and minimum area of the flow passage Cited by: 8.

“ An Analytical and Experimental Study of a Short S-Shaped Subsonic Diffuser of a Supersonic Inlet,” NASA TM, Washington, D.C., Link Google Scholar [13] Mark J.

L., McGarry M. and Reagan P. V., “ Research on a Two-Dimensional Inlet for a Supersonic V/STOL Propulsion System,” NACA CR, Google ScholarCited by: 7.

In addition to fixed and variable bleed devices provided for controlling the position of a terminal shock wave in a supersonic inlet, a plurality of free piston valves are disposed around the periphery of a cowling of a supersonic engine inlet.

The free piston valves are disposed in dump passageways, each of which begins at a bleed port in the cowling that is located in the throat region of Cited by:   The invention relates to the field of propulsion systems and, in particular, to a propulsion system for vertical and short takeoff and landing (V/STOL) aircraft.

DESCRIPTION OF RELATED ART. The efficiency of a propulsion system for an aircraft is maximized when the velocity of the exhaust gases equals the forward velocity of the aircraft. Abstract. A hypersonic inlet should be operated in a started mode for the efficient operation of an air-breathing propulsion system [1].

Various factors, either in design or in usage, may cause the hypersonic inlet to unstart, such as a large internal contraction ratio, low operating Mach number, delay of boundary layer transition, and high back pressure in the combustor, : Wenzhi Gao, Wenzhi Gao, Shuaitao Guo, Zhufei Li, Jiming Yang.

The normal shock wave/boundary-layer interaction is important to the operation and performance of a supersonic inlet, and the normal shock wave/boundary-layer interaction is particularly prominent in external compression inlets.

To improve understanding of such interactions, it is helpful to make use of fundamental flows that capture the main elements of inlets, without resorting to the level Cited by: 7. Propulsion within the lightcraft concept is produced via laser induced detonation of an incoming hypersonic air stream.

This process requires suitable engine configurations that offer good performance over all flight speeds and angles of attack to ensure the required thrust is maintained.

Stream traced hypersonic inlets have demonstrated the required performance in conventional hydrocarbon Cited by: 4. A Method for Comparing and Selecting Propulsion Systems for V/STOL Aircraft A systematic method for selecting the superior propulsion system for a V/STOL aircraft is presented.

A relatively well-defined set of aircraft requirements and a preselected group of candidate propulsion systems form the basis for the application of the by: 1. air intakes for air-consuming propulsion engines of supersonic aircraft filed feb. 23, 4 sheets-sheet l 1m. tam hm dec. 4, 1'. smith etal 3, air intakes for air-consuming propulsion engines 0f supersonic aircraft 4 sheds-sheet 2 filed feb.

25, fig. fig i mum, 23m. smith eial 3,Cited by:   The supersonic corner vortex in a generic hypersonic inlet/isolator model is theoretically and numerically analyzed at a freestream Mach number of The cross-flow topology of the corner vortex flow is found to obey Zhang’s theory [“Analytical analysis of subsonic and supersonic vortex formation,” Acta Aerodyn.

by:   Modern concepts of operation of supersonic inlets of high-velocity air-breathing engines are analyzed. It is demonstrated that the flow in the engine duct becomes extremely complicated in off-design modes of inlet operation, which can lead to unpredictable consequences, in particular, to inlet unstart.

The term “inlet unstart” is considered in the present paper as a synonym of the absence Cited by: 1. A magnetohydrodynamic drive or MHD accelerator is a method for propelling vehicles using only electric and magnetic fields with no moving parts, accelerating an electrically conductive propellant (liquid or gas) with fluid is directed to the rear and as a reaction, the vehicle accelerates forward.

The first studies examining MHD in the field of marine propulsion date. Each HSCT propulsion system unit—which consists of an air intake, turbofan engine, and exhaust nozzle—would be about 50 feet long, weigh 8 or 9 tons, and produce on the order of 60, pounds of thrust. (Figure illustrates the size of an HSCT propulsion system.) The design of the TCA (Technology Concept Aircraft) has four of these units.

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