3 edition of Hypersonic engine leading edge experiments in a high heat flux, supersonic flow environment found in the catalog.
Hypersonic engine leading edge experiments in a high heat flux, supersonic flow environment
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
Written in English
|Statement||Herbert J. Gladden and Matthew E. Melis.|
|Series||NASA technical memorandum -- 106742.|
|Contributions||Melis, Matthew E., United States. National Aeronautics and Space Administration.|
|The Physical Object|
The previous discussion related to an oblique shock formed over an ideal wedge with a perfectly sharp leading edge. In practical applications, however, the leading edge must be rounded or blunted in some way both for practicality of manufacture and to ease heat fluxes. Close to this blunt leading edge, the oblique shock becomes highly curved. The second model in our investigation is a 25°/55° cone/cone configuration with a sharp leading edge. The free stream conditions of this computation are U ∞ = m/s, T ∞ = K, P ∞ = Pa and ρ ∞ = × Kg/m corresponding Mach number is and the Reynolds number based on the length of the first cone is ×10 wall temperature also remains .
Stagnation point heat flux in hypersonic high enthalpy flow. Shock Waves, Vol. 2, No. 1 The mach number dependence of the stagnation point heat transfer in supersonic flow. International Journal of Heat and Mass Transfer, Vol. 18, No. 2 Investigation of an actively cooled leading edge for hypersonic ramjet engines. Characteristics of flow. While the definition of hypersonic flow can be quite vague and is generally debatable (especially due to the absence of discontinuity between supersonic and hypersonic flows), a hypersonic flow may be characterized by certain physical phenomena that can no longer be analytically discounted as in supersonic flow.
In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature by: Combined transpiration and opposing jet cooling could effectively cool the entire strut, especially the leading edge. The leading edge cooling efficiency increased from % for the leading edge without a slit to % for the leading edge with a mm wide slit when the coolant injection pressure was by: 7.
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NASA Technical Memorandum Hypersonic Engine Leading Edge Experiments in a High Heat Flux, Supersonic Flow Environment Herbert J. Gladden and Matthew E. Melis Lewis Research Center Cleveland, Ohio Prepared for the Winter Annual Meeting sponsored by the American Society of Mechanical Engineers Chicago, illinois, November ,File Size: 8MB.
Get this from a library. Hypersonic engine leading edge experiments in a high heat flux, supersonic flow environment. [Herbert J Gladden; Matthew E Melis; United States. National Aeronautics and Space Administration.]. Hypersonic engine leading edge experiments in a high heat flux, supersonic flow environment: Authors: A hydrogen/oxygen rocket engine heat source has been developed at the NASA Lewis Research Center as one element in a series of facilities at national laboratories designed to experimentally evaluate the heat transfer and structural response.
The specific objective of the experiment discussed is to evaluate the erosion and oxidation characteristics of a coating on a cowl leading edge (or strut leading edge) in a supersonic, high heat flux environment.
Heat transfer analyses of a similar leading edge concept cooled with gaseous hydrogen is included to demonstrate the complexity of Author: Matthew E. Melis and Herbert J. Gladden. Hypersonic engine component experiments in a high heat flux supersonic flow environment - NASA/ADS The major concern in advancing the state-of-the-art technologies for hypersonic vehicles is the development of an aeropropulsion system capable of withstanding the sustained high thermal loads expected during hypersonic by: 2.
The objective of the first experiment is to evaluate the erosion and oxidation characteristics of a coating on a cowl leading edge (or strut leading edge) in a supersonic, high heat flux environment.
Macrophotographic data from a coated leading edge model show progressive degradation over several thermal cycles at aerothermal conditions. 12 November Hypersonic engine component experiments in a high heat flux supersonic flow environment.
Research Center that is capable of providing heat fluxes up to W/cm 2 on flat surfaces and up to 5, W/cm 2 at the leading edge stagnation point of a strut in a supersonic flow stream.
Gas temperatures up to K can also be Cited by: 2. Hypersonic Engine Component Experiments in a High Heat Flux, Supersonic Flow Environment Herbert J. Gladden and Matthew E. Melis Lewis Research Center Cleveland, Ohio Prepared for the International Symposium on Optical Applied Science and Engineering sponsored by the Society of Photo-Optical Instrumentation Engineers.
The paper describes stagnation point heat flux measurements at a range of enthalpies relevant to re-entry speeds of aero-assisted space transfer vehicles (ASTVs) and proposed space planes, using the Australian National University Free Piston Shock Tunnel T3.
The unique feature of these experiments is that they were conducted in the ‘straight through’ Cited by: HYPERSONIC FLOWFIELD AND HEAT FLUX PECULIARITIES ON THE NEW SPACE LAUNCHER WITH WINGED REUSABLE FIRST STAGE 5 b) heat flux distribution. a) flow visualization Q= Figure 4. The WRRM model testing in the UT-1M wind tunnel at α=50 °, М=6, Re ≈9×10 6 Q Figure 5.
A computationally efficient, quasi-one-dimensional, supersonic combustion model has been developed to simulate high-speed engine flowfields such as in a scramjet. The model can be used in design and optimization studies, where a wide range of engine.
A transpiration cooling experiment using an optical heating method that provided a heat flux as high as W/cm(2) on the surface of specimen for a scramjet engine was performed. Simulation of Blunt Leading Edge Aerothermodynamics in Rarefied Hypersonic Flow problem since the heat flux for blunt bodies is far lower than that for sharply pointed bodies.
In addition, the reduction in heating rate for designing a hypersonic vehicle leading edge involves a. Survivability in the high temperature, high shear environment of hypersonic flow is a challenging endeavor for any sensor, particularly a MEMS device exposed to the flow.
As such, extensive cold testing, to calibrate the sensor, check out the various subsystems, the electronics, etc. were performed prior to hot-flow testing in aero-propulsion. The experiment will enable the time accurate investigation of the flow effects and their structural answer during the hypersonic flight from 90 km down to an altitude of 20 km.
Today’s experiments have shown that under hypersonic flow conditions, the leading-edge experiences a bow shock, a significant pressure rise, very large skin friction, and very large heat flux.
Further, these experimental observations have shown that adverse conditions are confined only to the by: 2. Higher local heat flux values are observed at all the leading edges of the cruise vehicle (i.e., nose, wing, fin and cowl leading edges) because of oblique shocks generated due to hypersonic flow on cruise vehicle.
Local heat flux increases in forebody and intake due external compression of high speed by: 1. Search the leading research in optics and photonics applied research from SPIE journals, conference proceedings and presentations, and eBooks Hypersonic engine component experiments in a high heat flux supersonic flow environment.
A computational-based investigation has been carried out to examine the heat transfer effects of normal and tangential blowing on blunt surfaces exposed to high Mach number flows. Experimental results from such studies where a controlled outflow is imposed upon a surface under hypersonic conditions are few and far between.
Simple 3D axisymmetric configurations Author: Mahmood Khalid, Khalid A. Juhany. An example of hypersonic experiments on sounding rockets is the NASA Sub-Orbital Aerodynamic Reentry EXperiment SOAREX program  to test future flight vehicles. SOAREX-1 was launched in on a Mk70 Terrier / BlackBrant IX rocket with a payload of 11 separate hypersonic experiments.
It. Interference heating effects generated by a blunt fin-type protuberance on a flat plate exposed to a hypersonic flow have been investigated experimentally and numerically.
Experiments and simulations were carried out at a free-stream Mach number of under laminar flow conditions.Because the leading edge affects flow and heat flux over the rest of the airfoil, the validation of the heat flux prediction was performed on a cylinder subjected to hypersonic flow.
The heat flux generated by hypersonic flow around a cylinder was predicted using the RANS flow solver and a semi-empirical equation proposed by Fay and Riddell [ 39 ].Cited by: 9.Experiments are carried out in the hypersonic vacuum wind tunnel V2G in Goettingen with a free stream condition, Ma ≈ 24 and Re 1 ≈ 10 4 at angles of attack 0° ≤ α ≤ 30° for the heat flux measurements and 0° ≤ α ≤ 40° for the force by: 1.