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Flow Analysis And Design Optimization Methods For Nozzle Afterbody Of A Hypersonic Vehicle
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722401399 Total Pages :64 pages Book Rating :4.4/5 (13 download)
Book Synopsis Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle by : National Aeronautics and Space Administration (NASA)
Download or read book Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes the methods developed for the aerodynamic analysis and the shape optimization of the nozzle-afterbody section of a hypersonic vehicle. Initially, exhaust gases were assumed to be air. Internal-external flows around a single scramjet module were analyzed by solving the three dimensional Navier-Stokes equations. Then, exhaust gases were simulated by a cold mixture of Freon and Argon. Two different models were used to compute these multispecies flows as they mixed with the hypersonic airflow. Surface and off-surface properties were successfully compared with the experimental data. In the second phase of this project, the Aerodynamic Design Optimization with Sensitivity analysis (ADOS) was developed. Pre and post optimization sensitivity coefficients were derived and used in this quasi-analytical method. These coefficients were also used to predict inexpensively the flow field around a changed shape when the flow field of an unchanged shape was given. Starting with totally arbitrary initial afterbody shapes, independent computations were converged to the same optimum shape, which rendered the maximum axial thrust. Baysal, Oktay Unspecified Center...
Book Synopsis Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle by : Oktay Baysal
Download or read book Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle written by Oktay Baysal and published by . This book was released on 1992 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle by : Oktay Baysal
Download or read book Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle written by Oktay Baysal and published by . This book was released on 1992 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis Experimental Results for a Hypersonic Nozzle/afterbody Flow Field by : Frank W. Spaid
Download or read book Experimental Results for a Hypersonic Nozzle/afterbody Flow Field written by Frank W. Spaid and published by . This book was released on 1995 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis Design Optimization of Hypersonic Test Facility Nozzle Contours Using Splined Corrections by :
Download or read book Design Optimization of Hypersonic Test Facility Nozzle Contours Using Splined Corrections written by and published by . This book was released on 2005 with total page 127 pages. Available in PDF, EPUB and Kindle. Book excerpt: A procedure is presented to design and optimize the contour of a hypersonic wind tunnel nozzle with a goal of minimizing exit flow nonuniformity. The procedure uses a Navier-stokes solver that admits chemical and vibrational nonequilibrium thermodynamics and high-pressure effects. The two-step optimization process is accomplished with a basic least-squares optimization (LSO) method. The first step of the design procedure begins with an existing inviscid irrotational method of characteristics (MOC) that is limited to thermally and calorically perfect gas (TCPG). MOC is used to design an inviscid contour, which is then corrected with a boundary layer displacement thickness from an integral momentum formulation. The deleterious effects of the TCPG assumption are ameliorated by using an effective specific-heat ratio an effective gas constant the TCPG computation yields the same exit Mach number and velocity as a quasi-one-dimensional computation based on thermochemical equilibrium. The MOC based contour is then formally optimized using the LSO method, treating various MOC program input variables as formal design parameters. The objective function is the square deviation of flow properties from target values at the nozzle exit, excluding the boundary layer, and is computed with the Navier-Stokes solver. The flow properties chosen for the objective function are the velocity components and the static pressure and density. After the MOC contour is optimized, the second step of the optimization procedure commences. In the second step, the contour is further perturbed by adding a small correction distribution represented as a cubic spline fitted to a limited number of nodes along the contour. The correction values of the nozzle radius are the formal design parameters for the next application of LSO.
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Book Synopsis Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects by : Ralph C. Tolle
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Book Synopsis Advances in Evolutionary and Deterministic Methods for Design, Optimization and Control in Engineering and Sciences by : Edmondo Minisci
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Book Synopsis Government Reports Announcements & Index by :
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