3 edition of Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow found in the catalog.
Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow
by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributors in Hampton, Va, [Springfield, Va
Written in English
|Statement||Michael S. Holden, John R. Moselle, and Jinho Lee.|
|Series||NASA contractor report -- 181893., NASA contractor report -- NASA CR-181893.|
|Contributions||Langley Research Center.|
|The Physical Object|
In the experimental program, detailed heat transfer and pressure measurements in laminar regions of shock wave/boundary layer interaction, and shock/shock interaction, over hollow cylinder/flare and double cone configurations in hypersonic Size: 2MB. Characteristics of the unsteady type IV shock/shock interaction of hypersonic blunt body flows are investigated by solving the Navier–Stokes equations with high-order numerical methods. The intrinsic relations of flow structures to shear, compression, and heating processes are studied and the physical mechanisms of the unsteady flow evolution are by: 8.
Abstract. Shock wave interaction occurs in many external and internal flow fields around hypersonic vehicles. The type IV shock interaction is one of the six types of shock interactions categorized by Edney  and is characterized by a supersonic jet embedded with the surrounding subsonic : F. S. Xiao, Zhufei Li, Yujian Zhu, Jiming Yang. The hypersonic type-IV shock interaction flow over a cylinder with a forward-facing cavity is experimentally and numerically investigated. Hypersonic Type-IV Shock_Shock .
The studies with multiple incident shocks demonstrate that the largest aerothermal loads are generated on the cylinder when the shocks coalesce before they are incident on the bow shock. Vortices are generated and shed off near the jet impingement point. “Viscous hypersonic shock‐on‐shock interaction on blunt cowl lips,” AIAA Paper No. 88–, “Shock wave interaction in hypervelocity flow,” Ph. D, thesis, California Institute of Technology, Cited by:
Close her eyes
On the establishment of a Graduate School at Oxford
Strategic plan, 2006-2009
Discourse delivered in Freeport, Maine, Feb. 10, 1809, at the funeral of Rev. Samuel Veazie ...
College Success Program
Understanding your living will
Landslides in the European Union
The divine authority of the Old and New Testament asserted: with a particular vindication of the characters of Moses, and the prophets, our saviour Jesus Christ, and his apostles, against the unjust aspersions and false reasonings of a book, entitled, The moral philosopher. By John Leland, ...
Carousel primary music
An a ccount of the countries adjoining to Hudsons Bay, in the north-west part of America
Memoirs of an ex-minister
Farming in the Brazilian Sertao
Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow. A review of the aerothermal characteristics of laminar, transitional, and turbulent shock/shock interaction regions in hypersonic flows.
Michael Holden. Experimental studies were conducted to examine the aerothermal characteristics of shock/shock/boundary layer interaction regions generated by single and multiple incident shocks. The presented experimental studies were conducted over a Mach number range from 6 to 19 for a range of Reynolds numbers to obtain both laminar and turbulent interaction regions.
Experimental studies of laminar separated flows induced by shock wave/boundary layer and shock/shock interaction in hypersonic flows for CFD validation Michael Holden 38th Aerospace Sciences Meeting and Exhibit August Experimental studies of laminar separated flows induced by shock wave/boundary layer and shock/shock interaction in hypersonic flows for CFD validation.
Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow. The complex flowfields and aerothermal loads generated by multiple-shock impingement, while not generating as large peak loads, provide important test cases for code prediction.
The detailed heat transfer and pressure measurements proved a good. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow.
distribution have been made in the present study of the aerothermal characteristics of regions of two-dimensional shock/shock interaction generated by the incidence of single and multiple shocks onto the bow shock ahead of a spanwise cylinder.
Studies of Aerothermal Loads Generated in Regions of Shock/Shock Interaction in Hypersonic Flow 26th Aerospace Sciences Meeting, Reno, NV, Jan.
11– /Author: Ashwani Assam, M. Nived, Nikhil Narayan Kalkote, Vinayak Eswaran. Experimental studies of laminar separated flows induced by shock wave/boundary layer and shock/shock interaction in hypersonic flows for CFD validation.
hypersonic flight environment, the same process is applicable to all systems experiencing aerothermal heating. The primary steps in aerothermal analysis and design include A.
System requirements definition B. Definition of aerothermal boundary conditions C. Identification of candidate material technology. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow (SuDoc NAS ) [Holden, Michael S.] on *FREE* shipping on qualifying offers.
Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow (SuDoc NAS )Author: Michael S. Holden. DSMC Computations for Regions of Shock/Shock and Shock/Boundary Layer Interaction James N.
Moss* "( NASA La'l_gley Research Center, Hampton, t')t This paper presents the results of a numerical study of hypersonic interacting flows at flow conditions that include those for which experiments have been conducted in the.
The investigation of shock/shock interaction in a 2D supersonic flow around a cylinder with an impinging shock generated by a wedge gives a good understanding of the processes affecting the surface heat transfer.
Depending on the relative coordinates of the point where the wedge shock crosses the cylinder bow shock. The reflected-shock tunnel has been used for some years now for the generation of short duration, high" enthalpy, hypersonic flow 1'2'3.
This paper gives an account of the pressure and temperature development with time in the region of the reflecting end of a hypersonic shock tunnel, using nitrogenFile Size: 3MB.
The compression waves thus generated coalesce to form a reat-tachment shock. Downstream of reattachment the shear-layer grows and the ﬂow becomes parallel to the surface. The sepa-rated shock may interact with the recompression shock forming a shock/shock interaction with the emergence of a slip line.
Geometric conﬁguration & Flow conditions. On the interference of a weak and a strong shock wave in a dissociating nitrogen flow.
Abstract. The influence of the nitrogen dissociation on the interactions due to the interference of two planar shock waves in a hypersonic high enthalpy flow is Cited by: 1. Get this from a library. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow.
[Michael S Holden; Langley Research Center.]. A.R. Wieting, M.S. Holden, J.R. Moselle, C. Glass — Studies of Aerothermal Loads Generated in Regions of Shock-Shock Interaction in Hypersonic Flow.
Cited by: 1. Experimental studies have been conducted to examine the characteristics of regions of shock wave/turbulent boundary layer interaction over cone/flare and hollow cylinder/flare configurations in high Reynolds number flows at Mach numbers between 5 and 10 in cold flows and in flows with duplicated flight velocities.
The flow properties behind the shock are related to freestream conditions via oblique shock relations and the equation of state. With the known pressure distribution along the wall, together with the assumed integrand functional form and behind-the-shock properties, the continuity and axial momentum equations are solved for shock standoff File Size: KB.
Request PDF | Study on Aerothermal Effects of Viscous Shock Interaction in Hypersonic Inlets | The objective of this study is to gain insight into the complex flow phenomena, governing the.
In hypersonic flows, the interaction of a shock wave with a turbulent boundary layer can result in flow separation and high aerothermal loads.Holden MS, Moselle JR, Lee J () Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow.
NASA-CR Google Scholar Hornung H () Non-equilibrium dissociating nitrogen flow over spheres and circular by: Studies of Aerothermal Loads Generated in Regions of Shock/Shock Interaction in Hypersonic Flows.
AIAA Paper3. D. Gaitonde, and J.S. Shang. The Performance of Flux-Split Algorithms in High-Speed Viscous Flows. AIAA Paper4. S. .