Validation of a CFD Solver for Hypersonic Flows PDF Download
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Author: Michael Charles Elford
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 195
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Book Description
Author: Michael Charles Elford
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 195
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724976987
Category :
Languages : en
Pages : 38
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Book Description
A roadmap for computational fluid dynamics (CFD) code validation is developed. The elements of the roadmap are consistent with air-breathing vehicle design requirements and related to the important flow path components: forebody, inlet, combustor, and nozzle. Building block and benchmark validation experiments are identified along with their test conditions and measurements. Based on an evaluation criteria, recommendations for an initial CFD validation data base are given and gaps identified where future experiments would provide the needed validation data. Marvin, Joseph G. Ames Research Center NASA-TM-103935, A-92091, NAS 1.15:103935 RTOP 505-59-00...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Jean Délery
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Julian D. Cecil
Publisher:
ISBN:
Category : Electronic dissertations
Languages : en
Pages : 37
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Book Description
This study aims to numerically simulate the wind tunnel results for hypersonic flow over a circular cone of semi-apex angle of 10 degrees yawed from 0° to 20° using the commercial computational fluid dynamics software ANSYS Fluent. The ANSYS workbench is used to create the 10° semi-apex circular cone with a shock aligned structured mesh of 3.05 million cells surrounding the cone. Simulation boundary conditions for pressure and temperature in the far field correspond to Tracy's wind tunnel experiment at Cal Tech. The six simulations cases are conducted for yaw angles of 0, 8, 12, 16, 20 and 24 degrees. The unsteady Reynolds-Averaged compressible Navier-Stokes solver with Spalart-Allmaras (SA) turbulence model is employed. The upstream flow Mach number is M = 8 and Reynolds number is Re00 = 4.2 x105 based on cone generator length. The maximum variation in static pressure computations around the cone is 7% of the experimental values and the maximum variation in heat transfer computations is within 12% of the experimental values; the maximum difference between the computations and experiment occurs at the leeward meridian of the cone. By further refinement of the mesh and using other turbulence models, it is possible that computational accuracy of the simulations may be further improved; however it requires additional investigation. Nevertheless the present simulations demonstrate that CFD can be employed with sufficient accuracy to compute the hypersonic flows about space vehicles with fully turbulent flow.
Author: William L. Oberkampf
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 49
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Book Description
Extensive surface pressure measurements were obtained on a hypersonic vehicle configuration at Mach 8. All of the experimental results were obtained in the Sandia National Laboratories Mach 8 hypersonic wind tunnel for laminar boundary layer conditions. The basic vehicle configuration is a spherically blunted 10° half-angle cone with a slice parallel with the axis of the vehicle. The bluntness ratio of the geometry is 10% and the slice begins at 70% of the length of the vehicle. Surface pressure measurements were obtained for angles of attack from -10 to + 18°, for various roll angles, at 96 locations on the body surface. A new and innovative uncertainty analysis was devised to estimate the contributors to surface pressure measurement uncertainty. Quantitative estimates were computed for the uncertainty contributions due to the complete instrumentation system, nonuniformity of flow in the test section of the wind tunnel, and variations in the wind tunnel model. This extensive set of high-quality surface pressure measurements is recommended for use in the calibration and validation of computational fluid dynamics codes for hypersonic flow conditions.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
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Author: Ioannis Nompelis
Publisher:
ISBN:
Category :
Languages : en
Pages : 324
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Book Description
Author: American Institute of Aeronautics and Astronautics
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN: 9781563472855
Category : Computational fluid dynamics
Languages : en
Pages : 0
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Book Description
This document defines a number of key terms, discusses fundamental concepts, and specifies general procedures for conducting verification and validation of computational fluid dynamics simulations. It's goal is to provide a foundation for the major issues and concepts in verification and validation. However, it does not recommend standards in these areas because a number of important issues are not yet resolved.
