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Friday, May 8, 2020 | History

2 edition of Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20 found in the catalog.

Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20

Francis J. Capone

Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20

by Francis J. Capone

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  • 29 Currently reading

Published by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Nozzles.,
  • Aerodynamics.

  • Edition Notes

    StatementFrancis J. Capone, Richard J. Re, and E. Ann Bare.
    SeriesNASA technical paper -- 3240., NASA technical paper -- 3240.
    ContributionsBare, E. Ann., Re, Richard J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.
    The Physical Object
    Pagination1 v.
    ID Numbers
    Open LibraryOL17750054M

      This article is divided into two parts. The first part focuses on the incompressible boundary layer. The general background of different flow structures and the limitation of visualization techniques are reviewed first (Sec. II), and the structures of incompressible flow are described in detail (Sec. III), including experimental and numerical visualization of structures, the similarity between Initial parametric studies involved a 5 to 20 degree wedged channel in Mach flow with varying pressure and temperature. A finite-volume algorithm was run with 2D Euler equations and a Rogers-Chinitz two-step hydrogen-oxygen reaction with five

    Parallel ramp injector geometry schematic. - O Swept I Unswept _ D T, = R ♦ O T, = R • O T, = R Equivalence ratio Figure Performance of swept and unswept ramps for Mach   Pye Wacket was the name of the cat who was the familiar to the witch played by Kim Novak in the film Bell Book and Candle. The comedy was released on Christmas day , with the love interest played by Strategic Air Command Colonel James Stewart (promoted to

       Results from Inch Mach 6 Air Tunnel Raised boundary layer trips and gouge At the beginning of the investigation the primary area of interest was early asymmetric boundary layer transition (ABLT), and in damage to the acreage tiles Web Site/CAIB/CAIB Website/CAIB. The wavelength agile aspect of the laser source allows for temperature insensitive measurements of oxygen concentration over a wide range of pressures ( atm to 50 atm). The system will also possess auto-calibration capabilities, the ability to withstand temporary immersion in all liquid fuels, fast time response (~ msec), and long


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Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20 by Francis J. Capone Download PDF EPUB FB2

Get this from a library. Parametric investigation of single-expansion-ramp nozzles at Mach numbers from to [Francis J Capone; Richard J Re; E Ann Bare; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Program.]   An investigation was conducted in the Langley Foot Transonic Tunnel to determine the effects of varying six nozzle geometric parameters on the internal and aeropropulsive performance characteristics of single-expansion-ramp nozzles.

This investigation was conducted at Mach numbers from tonozzle pressure ratios from to 12, and angles of attack of 0 deg +/- 6 deg. An investigation was conducted in the Langley Foot Transonic Tunnel to determine the effects of varying six nozzle geometric parameters on the internal and aeropropulsive performance characteristics of single-expansion-ramp nozzles.

This investigation was conducted at Mach numbers from tonozzle pressure ratios from to 12, and   In this paper, we present an experimental investigation of a supersonic rectangular nozzle with aft deck used for three-stream engines.

The jet utilizes a single expansion ramp nozzle (SERN) configuration along with multiple streams, operating at a bulk flow Mj,1 = and bypass stream Mj,3 = This idealized representation consists of two canonical flows: a supersonic convergent-divergent Parametric investigation of single-expansion-ramp nozzles at Mach numbers from to performance characteristics of single-expansion-ramp nozzles.

This investigation was conducted at   The authors would like to acknowledge the following organizations and individuals: our funding source, an SBIR Phase II and Phase I with AFRL turbine engine division under the direction of Dr.

Barry Kiel and an AFOSR Grant (FA) under the direction of Dr. Doug Smith; members of the Air Force noise team, Dr. Michael List, Christopher Norden, and Ryan Battelle; Dr. Junhui Liu and Dr 1.

Introduction. Over-expanded status is a primary status in supersonic nozzles, which occurs to a lower pressure ratio than design condition. For the nozzles of widely worked combined cycle engines, seriously over-expanded operating condition is easily occurring because operating pressure ratio variegating for a wide range and a high pressure ratio chosen at the design condition.

[6] Capone F J,Re R J,BareE tric Investigation of Single-Expansion-Ramp Nozzles at Mach Numbers from 0. 60 to [R].NASA-TP, [7] Capone F J,NASA TPRe R J,Bare E tric; Study of Single Expansion Ramp Time-resolved schlieren measurements were conducted on a supersonic rectangular multi-stream nozzle used for three-stream engines.

The jet utilizes a single expansion ramp nozzle (SERN) configuration along with an bypass stream, operating at an ideally expanded bulk flow of M j, 1 = and bypass stream of M j, 3 = Experiments were conducted with and without an aft deck to model airframe All these titles on 1 CD-Rom tmpdf - John N.

Shoosmith, Introduction to the LaRC Central Scientific Computing Complex, NASA TM (Revised), November, tmpdf - Butler, Ricky W. and Di Vito, Ben L., Formal Design and Verification of a Reliable Computing Platform for Real-Time Control (Phase 2 Results), NASA TM Compression and expansion ramp injectors.

A.- Perpendicular injection Combustion efficiency G/2 Tt = R Tt = R Tt = R X/G = 0 ° } B.-Parallel injection Unswept DCc X/G = X/G = 16 DC Tt = to R 0  › 百度文库 › 行业资料.

The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer This investigation was conducted at Mach numbers from tonozzle pressure ratios from to 12, and angles of attack of 0 deg +/- 6 deg.

Maximum aeropropulsive performance at a   The primary contaminant in the test gas is water vapor which varies from mole fraction at Mach 4 conditions to at Mach conditions.

A small amount of nitric oxide ( mole fraction) is also present in the test stream at the Mach  › 百度文库 › 行业资料.

A new design method of single expansion ramp nozzles under geometric constraints for scramjets Aerospace Science and Technology, Vol. 66 Melting, Processing and Characterization of NbWZr (Cb) Alloy Get this from a library. Aeropulsive characteristics at Mach numbers up to of axisymmetric and nonaxisymmetric nozzles installed on an F model.

[Francis J Capone; Langley Research Center.; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Branch.] -- An investigation to determine the aeropropulsive characteristics of nonaxisymmetric 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 /Design-and-Experimental-Study-of-an-Over-Under.

Publications related to the WIND-US CFD Code. The following is a list of technical papers and journal articles containing information related to the development and application of the WIND-US CFD code or one of its direct predecessor codes (WIND, NASTD, PARC, NPARC).

Propulsion integration of hypersonic air-breathing vehicles utilizing a top-down design methodology SERN Single Expansion Ramp Nozzle.

xi ACKNOWLEDGMENTS First of all, I would like to thank my family, friends, and fellow graduate students. hypersonic flight refers to flight at high Mach numbers. However, what defines hypersonic flight ?article=&context=etd. Parametric study of the performance and beam quality of cesium DPAL: experiment and modelling.

Ilya Auslender, Eyal Yacoby, Boris Barmashenko, Salman Rosenwaks. Proc. SPIE.XXII International Symposium on High Power Laser Systems and Applications.

KEYWORDS: Modeling, Resonators, Lasers, Laser resonators, Modes of laser operation, Cesium. Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to Jun 1, 06/ by These configurations simulated the variable-geometry features of two nozzle designs designated as the multiple-expansion ramp nozzle (MERN) and the composite contour nozzle (CCN).

A parametric investigation ?and[]=subject:"Orientation".Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging.

The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves. The detonation wave initiation in detonation tube in   ACCIDENT INVESTIGATION BOARD.

COLUMBIA. ACCIDENT INVESTIGATION BOARD. COLUMBIA. Rick Husband, Commander. Husband, 45, was a Colonel in the U.S. Air Force, a test pilot, and a veteran of STS He