Hypersonic Flow Over a Yawed Circular Cone PDF Download
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Author: Richard Ripley Tracy
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 270
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Book Description
Author: Richard Ripley Tracy
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 270
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Book Description
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: Willis H. Braun
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: Richard R. Tracy
Publisher:
ISBN:
Category :
Languages : en
Pages : 135
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Book Description
Author: Joseph W. Cleary
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 52
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Book Description
Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 106
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Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Robert H. Feldhuhn
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 82
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Book Description
An experimental investigation illustrating some separated flow phenomena associated with highly inclined circular cones was conducted at a nominal Mach number of 5 and at nominal free stream Reynolds numbers per foot of 4,800,000. Surface static pressure measurements, Pitot pressure surveys, schlieren photographs, vapor screen photographs, and surface sublimation measurements were obtained on a sharp 5 degree semi-vertex angle cone at angles of attack up to 40 degrees. The static pressure distribution along the most leeward meridian generator was found to be dependent upon the Reynolds number based upon the distance from the vertex of the cone. The vapor screen photographs at 40 degrees angle of attack indicate the existence of imbedded shock waves in the flow field on the leeward side of the cone. The Pitot tube surveys and the surface sublimation photographs indicate the existence of a region of attached flow near the leeward meridian plane. The surface sublimation photographs also indicate the possible existence of a secondary vortex. (Author).
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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Book Description
The results of the calculation of supersonic flow of helium about right circular cones at zero angle of attack are presented in tabular form. The calculations were performed using the Taylor-Maccoll theory. Numerical integrations were performed using a Runge-Kutta method for second-order differential equations. Results were obtained for cone angles from 2.5 to 30 degrees in regular increments of 2.5 degrees. In all calculations the desired free-stream Mach number was obtained to five or more significant figures.
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 440
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Book Description
Author: John J. Bertin
Publisher: AIAA
ISBN: 9781563470363
Category : Science
Languages : en
Pages : 644
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Book Description
A modern treatment of hypersonic aerothermodynamics for students, engineers, scientists, and program managers involved in the study and application of hypersonic flight. It assumes an understanding of the basic principles of fluid mechanics, thermodynamics, compressible flow, and heat transfer. Ten chapters address: general characterization of hypersonic flows; basic equations of motion; defining the aerothermodynamic environment; experimental measurements of hypersonic flows; stagnation-region flowfield; the pressure distribution; the boundary layer and convective heat transfer; aerodynamic forces and moments; viscous interactions; and aerothermodynamics and design considerations. Includes sample exercises and homework problems. Annotation copyright by Book News, Inc., Portland, OR
