by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English
|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|
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 Paper , Oct. 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.