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Sunday, July 26, 2020 | History

4 edition of Internal performance characteristics of thrust-vectored axisymmetric ejector nozzels found in the catalog.

Internal performance characteristics of thrust-vectored axisymmetric ejector nozzels

Internal performance characteristics of thrust-vectored axisymmetric ejector nozzels

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Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English


Edition Notes

Other titlesInternal performance characteristics of thrust vectored axisymmetric ejector nozzels.
StatementMilton Lamb.
SeriesNASA technical memorandum -- 4610.
ContributionsLangley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17012393M
OCLC/WorldCa33154737

  The history of rocket nozzles, specifically rao nozzle comes from G. V. Rao back in , when he derived analytically the wall contour of a nozzle by method of characteristics (Reference 1). The bell contour shape nozzle minimized the losses of the internal shock waves in the supersonic flow. Internal nozzle performance (wind-off conditions) and thrust vector angles were computed for several configurations over a range of nozzle pressure ratios from to 10, with the fluidic injection flow rate equal to zero and up to 4 percent of the primary flow rate. The effect of a variable expansion ratio on nozzle performance over a range.

This work deals with theoretical aspects of thrust vector control in rocket nozzles by the injection of secondary gas into the supersonic region of the nozzle. The work is concerned mainly with two-dimensional flow, though some aspects of three-dimensional flow in axisymmetric nozzles are considered. The subject matter is divided into three parts. Performance of a thrust-vectoring solution for unmanned air vehicles was conducted. Influence of the cover nozzle on the engine operating line and the performance of the vectoring system compared.

Investigations on infrared (IR) radiation suppression of axisymmetric vectoring exhaust nozzle (AVEN) are meaningful, due to the requests for maneuverability and IR stealth capability of aircrafts. In this paper, the synthetic suppression scheme of film cooling and low-emissivity coating was adopted on the center body and divergent flaps of the. An experimental studyis carried outto investigate the characteristics of apulsed-jet ejector thrust augmentor that is suitable for use in vertical take-off and landing aircraft.


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Internal performance characteristics of thrust-vectored axisymmetric ejector nozzels Download PDF EPUB FB2

A series of thrust-vectored axisymmetric ejector nozzles were designed and experimentally tested for internal performance and pumping characteristics at the NASA Langley Research Center. These ejector nozzles used convergent-divergent nozzles as the primary noz-zles.

The model geometric variables investigated were. BibTeX @MISC{Axisymmetric95internalperformance, author = {Thrust-vectored Axisymmetric and Ejector Nozzles and Milton Lamb and Thrust-vectored Axisymmetric and. A series of thrust-vectored axisymmetric ejector nozzles were designed and experimentally tested for internal performance and pumping characteristics at the Langley research center.

This study indicated that discontinuities in the performance occurred at low primary nozzle pressure ratios and that these discontinuities were mitigated by Author: Milton Lamb.

A series of vectoring axisymmetric ejector nozzles were designed and experimentally tested for internal performance and pumping characteristics at NASA-Langley Research Center. These ejector nozzles used convergent-divergent nozzles as the primary nozzles.

and thrust vector angle. The primary nozzle pressure ratio was varied from to 10 Author: Milton Lamb. Internal Performance Characteristics of. By Thrust-vectored Axisymmetric, Ejector Nozzles and Milton LambThrust-vectored Axisymmetric, Ejector Nozzles and Milton Lamb. Abstract. Printed copies available from the following Topics: Contents.

Side-Force Amplification on an Aerodynamically Thrust-Vectored Aerospike Nozzle. Internal performance characteristics of vectored axisymmetric ejector nozzles.

MILTON LAMB; 29th Joint Propulsion Conference and Exhibit August   Dynamic response of an axisymmetric thrust vector control nozzle.

Internal performance characteristics of vectored axisymmetric ejector nozzles. MILTON LAMB; 29th Joint Propulsion Conference and Exhibit August 29th Aerospace Sciences Meeting. 07 January - 10 January   Aircraft performance sensitivities to ejector nozzle concepts.

Internal performance characteristics of vectored axisymmetric ejector nozzles. MILTON LAMB; 29th Joint Propulsion Conference and Exhibit August   Performance characteristics of nonaxisymmetric nozzles installed on the F aircraft Internal performance characteristics of vectored axisymmetric ejector nozzles.

MILTON LAMB; 29th Joint Propulsion Conference and Exhibit August Summary of nonaxisymmetric nozzle internal performance from the NASALangley Static Test Facility. Abstract: A key aspect of the preliminary design process for a new generation combat aircraft is the prediction of afterbody aerodynamic drag.

Current prediction methods for preliminary design are constrained in terms of number of independent geometric degrees of freedom that can be studied due to the classic circular arc or conical afterbody geometry parametrization. Internal performance characteristics of thrust-vectored axisymmetric ejector nozzels.

[Milton Lamb; Langley Research Center.] Home. WorldCat Home About WorldCat Help. Search. Search for Library Items Search for Lists Search for Contacts Book\/a>, schema:CreativeWork\/a>, bgn. The results obtained show that unvectored performance of the cruciform nozzle is only slightly lower ( to percent) than that of previously tested axisymmetric and nonaxisymmetric nozzles.

In order to investigate the ejector performance, the ejector refrigeration system (ERS) designed and operated by Hamzaoui et al. [] was used in the present work with different ejector 1 represents a schematic diagram of the experimental set up which consists of an ERS and three auxiliary utility circuits: a heating loop, a cooling loop and a thermal load loop.

An axisymmetric version of the Dual Throat Nozzle concept with a variable expansion ratio has been studied to determine the impacts on thrust vectoring and nozzle performance.

The nozzle design, applicable to a supersonic aircraft, was guided using the unsteady Reynolds-averaged Navier-Stokes computational fluid dynamics code, PAB3D.

The. Static internal performance of an axisymmetric nozzle with multiaxis thrust-vectoring capability [microform] / George T. Carson, Jr., and Francis J. Capone National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; For sale by the National Technical Information Service] Washington, D.C.

The geometry and operation parameters have important influences on the performance of steam ejectors. An axisymmetric two-dimensional mathematical model for transonic compressible flow inside a steam ejector has been established in this paper to investigate the flow characteristics inside steam ejectors aiming at optimizing primary steam nozzle exit section distance and mixing chamber throat.

An axisymmetric divergent DTN (ADDTN, the expansion ratio (A 2 / A 1) is greater than 1) was investigated computationally and experimentally at NASA LaRC in to improve thrust performance within the full flight envelope, particularly under high nozzle pressure ratio (NPR) and Mach number conditions.However, the results of the study conducted at NASA LaRC indicated that the.

The operational mode performance was studied in the ejectors with multiple axisymmetric and notched nozzles placed in several layers along the peripheral direction. The results showed that an appropriate number of nozzles could improve the ejection performance and decrease the scale of ejectors.

The expansion waves from the nozzle exit strengthen the driving flow expansion, which creates a negative effect on ejector performance. However, with an appropriate nozzle design, the performance of the ejector can be enhanced.

Under the off-design condition, d max deviates from the predicted value according to the isentropic expansion. Comparison of axisymmetric (top) and 2D (bottom) nozzles. Two-dimensional nozzles, on the other hand, are capable of not only directing the thrust along the axis of the engine, but can deflect to vector the thrust and produce a force that points the nose of the plane in a different direction.

This type of nozzle is at the heart of what is known. A propelling nozzle is a nozzle that converts the internal energy of a working gas into propulsive force; it is the nozzle, which forms a jet, that separates a gas turbine, being gas generator, from a jet engine. Propelling nozzles accelerate the available gas to subsonic, transonic, or supersonic velocities depending on the power setting of the engine, their internal shape and the pressures.A jet nozzle of a gas turbine engine with thrust vector deflection contains a circular cross-section body with tapering crowns and pivotally connected therewith extending folds and coaxially located with the housing air ejector made in the form prescribed for the output cutoff valves corps nozzle two coaxially arranged annular rings and pivotally interconnected crowns internal and external.Internal nozzle performance (wind-off conditions) and thrust vector angles were computed for several configurations over a range of nozzle pressure ratios from to 10, with the fluidic.