by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English
|Series||NASA technical memorandum -- 106233.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Get this from a library! Small hydrogen/oxygen rocket flowfield behavior from heat flux measurements. [B D Reed; United States. National Aeronautics and Space Administration.]. In this study, normal heat flux profiles in a small gaseous hydrogen/gaseous oxygen rocket were determined as a diagnostic of the flowfield behavior. A thick- walled, water-cooled OFHC copper rocket chamber, instrumented with thermocouples, was used to gather steady-state, inner and outer wall temperature profiles over a mixture ratio range from to , at sixty percent fuel film cooling. A Rayleigh scattering diagnostic has been developed to measure gas density, temperature, and velocity in the exhaust plume of N thrust class hydrogen-Oxygen rockets. Circumferential Behavior of Tangential Film Cooling and Injector Wall Compatibility in a High Pressure LOX/GH2 Subscale Combustion Chamber. Measurement and Analysis of Heat Transfer in a Multi-Element Hydrogen/Oxygen Rocket Combustor. Mauritz deRidder, David Helderman.
Isolated fluid oxygen drop behavior in fluid hydrogen at rocket chamber pressures. J i, and the heat flux, q, to thermodynamic quantities. Conservation equations. under supercritical conditions Le is a misleading measure of the flux by: A small laboratory diagnostic thruster was developed to augment present low thrust chemical rocket optical and heat flux diagnostics at the NASA Lewis Research Center. Table 1 summarizes all available burning velocity measurements of hydrogen flames using the heat flux method at atmospheric pressure. Most of the mixtures studied were diluted because the heat flux method is not suitable for measuring flames that are too fast; a typical limit is about 60 cm/s as discussed in details by Alekseev et by: 7. I. Introduction. C hemical rocket engines represent the only propulsion system that is able to transport payload into the Earth orbit. The combination of liquid oxygen (LOX) and liquid hydrogen (LH2) has been investigated since the s and is used in many first- and upper-stage engines (such as Vulcain, Vinci, SSME, and RD).Cited by: 1.
Water is composed of two Hydrogen atoms, and one Oxygen atom. This is because Oxygen has six valence electrons (valence electrons are the electrons in the furthest shell of an atom. They are the ones who get all the action in chemical reactions,) and Hydrogen has one. Thats when the saying "eight is the great" comes in. Full text of "NASA Technical Reports Server (NTRS) NASA Propulsion Engineering Research Center, volume 2" See other formats. presentation summarizes the purpose, design, and initial test results of these small rocket flowfield diagnostic chambers. HEAT FLUX DIAGNOSTIC CHAMBER A chamber was designed and fabricated to determine steady-state heat flux to the inner wall to be used as a diagnostic of the flowfield behavior, l The heat flux chamber design is an instrumented, water-cooled chamber used. 8. Put a small lump of aluminium foil in the test tube 9. Measure 20 cm3 of sodium hydroxide (6 M) solution onto the foil in the test tub Stopper the test tube Put the plastic pipette in the bottle and allow it to half-fill with hydrogen as shown below. NB – the hydrogen:oxygen mixture must be If there is too much hydrogen it can File Size: KB.