3 edition of A unique high heat flux facility for testing hypersonic engine components found in the catalog.
A unique high heat flux facility for testing hypersonic engine components
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
|Statement||Matthew E. Melis and Herbert J. Gladden.|
|Series||NASA technical memorandum -- 103238.|
|Contributions||Gladden, Herbert J., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Unique and specialized instrumentation is designed, fabricated, calibrated, and installed in supersonic and hypersonic test articles and facilities. A wide range of heat-flux transducer and temperature measurement methodologies have been modeled with state-of-the-art finite element analysis (FEA) tools, and instrumentation subsequently. applications, and the current status of scramjet engines. Definition of a scramjet engine In order to provide a definition of a scramjet engine, the definition of a ramjet engine is first necessary, as a scramjet engine is a direct descendant of a ramjet engine. Ramjet engines have no moving parts unlike turbojets or turbofans. It is.
aero-thermo-structural testing related to hypersonic flight that presented new challenges. When the experimental rocket plane began flying, the center established the Heat Facility in an earlier iteration, located in a corner of the Loads Calibration Hangar, or what today is known as Hangar That facility . This video gives an overview of the High Heat Flux Facility being built at Stennis Space Center in conjunction with Wright-Patterson Air Force Base. This facility will simulate flight heat.
The new material enables a hypersonic aircraft to fly at Mach within the atmosphere for several hours, as the high heat resulting from the friction between the aircraft and the air reaches. Schematic of a Heat Pipe Cooled Leading Edge with an Active 23 Internal Heat Exchanger Schematic of the Heat Pipe Cooling Model Energy Balance 27 A Typical Hypersonic Vehicle Ascent Flight Trajectory 41 A Typical Hypersonic Vehicle Velocity-Altitude Map 42 Aerodynamic Surface Heat Flux Distribution, Chordwise
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A UNIQUE HIGH HEAT FLUX FACILITY FOR TESTING HYPERSONIC ENGINE COMPONENTS Matthew E. Melis and Herbert J. Gladden National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio It Abstract A major concern in advancing the state-of-the-art technologies for hypersonic vehicles is the.
Get this from a library. A unique high heat flux facility for testing hypersonic engine components. [Matthew E Melis; Herbert J Gladden; United States.
National Aeronautics and Space Administration.]. This paper describes the Hot Gas Facility, a unique, reliable, and cost-effective high-heat-flux facility for testing hypersonic engine components developed at the NASA Lewis Research Center.
The Hot Gas Facility is capable of providing heat fluxes ranging from Btu/sq ft per sec on flat surfaces up to Btu/sq ft per sec at a leading Author: Matthew E. Melis and Herbert J. Gladden. system components in the SSME test bed engine.
TFTC's were successfully fabricated on flat coupons of MAR-M (+Hf), hydrogen-oxygenrocket engine facility located at the NASALewis Research M.E.; and Gladden, H.J.: A Unique High Heat Flux Facility for Testing Hypersonic Engine Components.
AIAA PaperOct. Basic Thin. Impulse hypersonic test facilities like the shock tunnel are commonly used for such estimation tests. The present paper compares contemporary heat flux measurement techniques, namely, E‐type coaxial thermocouples, Pt‐thin films, and atomic layer thermopiles in a hypersonic shock tunnel at the base of a scaled‐down re‐entry : Kiran J.
Irimpan, Viren Menezes, K. Srinivasan. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Weight drives components to be clustered near engine Arc-jet test of DLR C/C-SiC for X at NASA JSC Time, sec Arc-jet test of MT Aerospace C/SiC in the High heat flux/temperature Reduced fuel.
vehicles and hypersonic cruise vehicles. This vehicle with advanced airbreathing engines would have the capability to take off horizontally from and land on conventional runways, accelerate to orbit, and cruise hypersonically in the atmosphere between Earth destinations.
(NASA Art Program, Image HC). Facing the Heat Barrier. Unique and specialized instrumentation is designed, fabricated, calibrated, and installed in supersonic and hypersonic test articles and facilities. A wide range of heat-flux transducer and temperature measurement methodologies have been modeled with state-of-the-art finite element analysis (FEA) tools, and instrumentation subsequently.
The maximum heat flux on the front face of the heat shield was kW/m 2 during a period of 20 seconds, and on the rear face the heat flux was between 30 kW/m 2 and kW/m 2. The constituents of Titan’s atmosphere are nitrogen (77%), argon (20%) and methane (3%).
In order to investigate the accuracy of the rebuilding code for the free stream conditions and the total enthalpy in the Longshot Hypersonic facility at the von Karman Institute (VKI), a series of unsteady CFD simulations of axisymmetric hypersonic flow over a heat flux probe have been performed.
The engine can be operated continuously from take-off to Mach 5. This engine uses a pre-cooling cycle using cryogenic liquid hydrogen. The high temperature inlet air of hypersonic flight would be cooled by the same liquid hydrogen used as fuel.
The engine is tested under sea level static conditions. The engine is installed on a flight test vehicle. This paper presents detailed heat flux measurements on a flat plate subjected to the ISO [The International Organization for Standardization (ISO),“Aircraft—Environmental Conditions and Test Procedures for Airborne Equipment—Resistance to Fire in Designated Fire Zones,” ISO(E)] standard, propane fueled burner used throughout the industry in aero-engine fire.
Thin-film heat flux gauges (HFGs) have been used for decades to measure surface temperatures and heat flux in test turbines with the majority being used in facilities that are sho. 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.
Motivation For Hypersonic Flight Testing • Developing a hypersonic vehicle requires an extensive high-fidelity design database • Database must contain fundamental and system-level performance data that cannot be gathered completely in existing ground test facilities or [currently] by simulation • Flight Testing Required.
Therefore, there is a need to develop innovative, affordable thermal/mechanical test methods under a relevant hypersonic operational environment.
The target hypersonic environment ranges between Mach The environment must recreate operational conditions including temperature, heat flux, thermal/pressure loading, atmosphere and plasma.
The CPTF will meet the similar heat load conditions of the CFETR operation to certify feasibility, reliability, rationality and efficiency of the PFCs manufacturing techniques for CFETR and the future high heat load components. Currently, several high heat flux facilities with electron beam (EB) test stands were constructed to test the PFC.
Hypervelocity Ground Test Facilities 80 A. Introduction 80 B. Design and Operation of the LENS I and II Shock Tunnels. 80 C. Aerothermal, Aero-Optic, and Radiation Instrumentation, Suites 82 IV. Facility Validation: 86 V. Application of Test Facility and Instrumentation to Hypersonic Vehicle Testing 90 A.
Evaluation of the Aerothermal and. Engages in research, development, and flight application of advanced materials, structures, and mechanisms for aerospace systems, with activities ranging from materials research at nanoscale to design and testing of structures and mechanical systems for aeronautics and space flight programs.
Research and development activities are focused on developing enabling technologies for high. Abstract High heat flux test facility (HHFTF) at IPR is used for testing thermal performance of plasma facing materials or components.
It consists of various subsystems like vacuum system, high power electron beam system, diagnostic and calibration system, data acquisition and control system and high pressure high temperature water circulation system.hydrogenioxygen rocket engine has been modified to establish a high enthalpy/high heat flux environment.
The facility is capable of providing heat flux levels from about up to 10 Btu/ft'/sec. Crossflow and parallel flow regenera- tively cooled models can be tested and analyzed by using.For high heat flux applications such as heat shields and nozzle liners, carbon/phenolic ablators are infiltrated into open-cell carbon foam.
Relative to conventional ablators, foam-reinforcement foam reinforcement enhances surface char layer retention and reduces erosion and heat transfer.
Density is variable from lb/ft 3.