Hypersonic Flow Over Closed and Open Nose Missile Bodies PDF Download
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Author: Russell Keanini
Publisher:
ISBN:
Category : Electronic books
Languages : en
Pages : 0
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Book Description
Understanding and mitigating against high heat loads at leading and blunt aerodynamic surfaces during hypersonic flight represents an ongoing technological challenge. Recent work has shown that the commercial software package, STAR CCM+, can provide reliable predictions of hypersonic aerothermodynamic flow and heating, under a wide range of complex, but common conditions. This chapter presents a preliminary experimental and numerical investigation of hypersonic flow over closed- and open-nose missile bodies, where the latter have been proposed as a means of reducing leading edge heat transfer. Four contributions are presented. First, a novel singular value decomposition (SVD)-based image processing technique is introduced, which significantly enhances the quality of raw schlieren images obtained in high-speed compressible flows. Second, numerically predicted hypersonic flow about a scale-model missile body, obtained using STAR-CCM+, is validated against experimental schlieren image data, an empirical correlation connecting bow shock stand-off distance and shock density ratio, and estimated drag forces. Third, scaling and physical arguments are presented as a means of choosing appropriate gas equations of state and for interpreting results of numerical simulations and experiments. Last, numerical experiments show that the forward facing cavity used in our wind tunnel experiments functions as a heat sink, reducing heat fluxes on the missile body downstream of the cavity.
Author: Russell Keanini
Publisher:
ISBN:
Category : Electronic books
Languages : en
Pages : 0
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Book Description
Understanding and mitigating against high heat loads at leading and blunt aerodynamic surfaces during hypersonic flight represents an ongoing technological challenge. Recent work has shown that the commercial software package, STAR CCM+, can provide reliable predictions of hypersonic aerothermodynamic flow and heating, under a wide range of complex, but common conditions. This chapter presents a preliminary experimental and numerical investigation of hypersonic flow over closed- and open-nose missile bodies, where the latter have been proposed as a means of reducing leading edge heat transfer. Four contributions are presented. First, a novel singular value decomposition (SVD)-based image processing technique is introduced, which significantly enhances the quality of raw schlieren images obtained in high-speed compressible flows. Second, numerically predicted hypersonic flow about a scale-model missile body, obtained using STAR-CCM+, is validated against experimental schlieren image data, an empirical correlation connecting bow shock stand-off distance and shock density ratio, and estimated drag forces. Third, scaling and physical arguments are presented as a means of choosing appropriate gas equations of state and for interpreting results of numerical simulations and experiments. Last, numerical experiments show that the forward facing cavity used in our wind tunnel experiments functions as a heat sink, reducing heat fluxes on the missile body downstream of the cavity.
Author: John V. Rakich
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
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Book Description
Author: Vallampati Ramachandra Prasad
Publisher: BoD – Books on Demand
ISBN: 1803562188
Category : Technology & Engineering
Languages : en
Pages : 264
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Book Description
This book provides a comprehensive overview of boundary layer flows, including laminar and turbulent flows. Chapters discuss such topics as the nature of transition, the effect of two-dimensional and isolated roughness on laminar flow, and progress in the design of low-drag airfoils. They also present theoretical and experimental results in boundary layer flows and discuss directions for future research.
Author: G. G. Chernyi
Publisher: Academic Press
ISBN: 1483271684
Category : Technology & Engineering
Languages : en
Pages : 277
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Book Description
Introduction to Hypersonic Flow has been made available to the English speaking reader because of its usefulness for those individuals desirous of obtaining an introduction to the subject. Written by an internationally acknowledged expert in the field of hypersonic flow, the book makes available heretofore unpublished Soviet work, as well as published work little known outside the Soviet Union. The author has however made every effort to include, where appropriate. Western references for the work he discusses. Starting with a general introductory chapter on hypersonic aerodynamics and aerodynamic problems, the remainder of the book concentrates on the inviscid, perfect fluid aspects of hypersonic flow, with emphasis on the fundamental concepts and rational methods of calculation. The book is directed to students of aerodynamics and gas dynamics, as well as to scientists and engineers interested in problems of hypersonic flight. The level of approach is such that it should prove particularly useful as an undergraduate and introductory graduate text.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723186646
Category :
Languages : en
Pages : 126
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Book Description
Hypersonic flows over cones and straight biconic configurations are calculated for a wide range of free stream conditions in which the gas behind the shock is treated as perfect. Effect of angle of attack and nose bluntness on these slender cones in air is studied extensively. The numerical procedures are based on the solution of complete Navier-Stokes equations at the nose section and parabolized Navier-Stokes equations further downstream. The flow field variables and surface quantities show significant differences when the angle of attack and nose bluntness are varied. The complete flow field is thoroughly analyzed with respect to velocity, temperature, pressure, and entropy profiles. The post shock flow field is studied in detail from the contour plots of Mach number, density, pressure, and temperature. The effect of nose bluntness for slender cones persists as far as 200 nose radii downstream. Sehgal, A. K. and Tiwari, S. N. and Singh, D. J. Unspecified Center ANGLE OF ATTACK; BLUNT BODIES; FLOW DISTRIBUTION; HYPERSONIC FLOW; NOSE CONES; SLENDER CONES; VISCOUS FLOW; AERODYNAMIC CONFIGURATIONS; AIR FLOW; ENTROPY; FLOW VELOCITY; FREE FLOW; MACH NUMBER; NAVIER-STOKES EQUATION; PRESSURE EFFECTS; TEMPERATURE EFFECTS; TEMPERATURE PROFILES...
Author: Frederick R. Riddell
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 776
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Book Description
Author: Raymond L. Barger
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
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Book Description
Three missile body shapes tested at Mach numbers of 1.50, 2.16, and 2.86 with angles of attack up to 30 degrees are described. The flow characteristics for each body shape are examined. The measured aerodynamic forces and moments are presented. The use of flow visualization techniques are described and the results such as vortex effects are discussed.
Author: D.J. Singh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: D. J. Singh
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 144
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Book Description
Author: T. A. Heppenheimer
Publisher: Government Printing Office
ISBN: 9780160831553
Category : Business & Economics
Languages : en
Pages : 358
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Book Description
Hypersonics is the study of flight at speeds where aerodynamic heating dominates the physics of the problem. It is an engineering science with close links to supersonics and engine design. Within this field, many of the most important results have been experimental. The principal facilities have been wind tunnels and related devices, which have produced flows with speeds up to orbital velocity. Why is this important? Hypersonics has had two major applications. The first has been to provide thermal protection during atmospheric reentry. Success in this enterprise has supported ballistic-missile nose cones, has returned strategic reconnaissance photos from orbit and astronauts from the Moon, and has even dropped an instrument package into the atmosphere of Jupiter. The second application has involved high-speed propulsion and has sought to develop the scramjet as an advanced airbreathing ramjet. Atmospheric entry today is fully mature as an engineering discipline, but work with its applications continues to reach for new achievements. Studies of scramjets still seek full success, in which such engines can accelerate a vehicle without the use of rockets. Hence, there is much to do in this area as well.
