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Saturday, November 14, 2020 | History

1 edition of Experimental investigation of temperature and velocity distribution about a rocket jet found in the catalog.

Experimental investigation of temperature and velocity distribution about a rocket jet

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Published by California Institute of Technology .
Written in English

    Subjects:
  • Aeronautics

  • Edition Notes

    Thesis (AE)--California Institute of Technology, 1947.

    ID Numbers
    Open LibraryOL24704402M

    Dunn, Louis G. () An experimental investigation of the stresses in extruded sections commonly used in aircraft construction. Master's thesis, California Institute of Technology. Dunn, Louis G. () An investigation of sheet-stiffener panels subjected to compression loads with particular reference to torsionally weak stiffeners. A study of the jet that is one of a representative flow field of free shear flow has been done a lot so far, and the engineering application field is wide. There are various kinds for a three-dimensional free jet from a difference of shape of an outlet. Of these, a circular jet [1], an elliptical jet [2], a rectangular jet [3]. 2 in excess of 3× with exit Mach numbers up to and total temperatures up to K. The M d=, convergent-divergent nozzle used in this study has a rectangular exit with aspect ratio and 10 mm in short dimension. Velocity Field Measurements Velocity field data were obtained by means of . CiteScore: ℹ CiteScore: CiteScore measures the average citations received per peer-reviewed document published in this title. CiteScore values are based on citation counts in a range of four years (e.g. ) to peer-reviewed documents (articles, reviews, conference papers, data papers and book chapters) published in the same four calendar years, divided by the number of.


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Experimental investigation of temperature and velocity distribution about a rocket jet by Quentin Robert Whitmore Download PDF EPUB FB2

The purpose of the investigation was to determine the temperature distribution and velocity profile surrounding the wake of a pound thrust liquid rocket motor.

The temperature measurements were restricted to those °F and below. The velocities measured were in the region in which the temperature measurements were made. The region in which the temperatures exceeded °F was. Experimental investigation of temperature and velocity distribution about a rocket jet.

purpose of this investigation was to determine the temperature distribution and velocity profile surrounding the wake of a pound thrust liquid rocket motor.

The temperature measurements were restricted to those degrees F and : Quentin Robert Whitmore. Experimental investigation of temperature and velocity distribution about a rocket jet. By Quentin Robert Whitmore. Download PDF (21 MB) Abstract. The purpose of the investigation was to determine the temperature distribution and velocity profile surrounding the wake of a pound thrust liquid rocket Author: Quentin Robert Whitmore.

The mean values of all three velocity components and the three normal fluctuating Reynolds stresses as well as the mean temperature have been measured in a large number of points surrounding the central injection hole.

Experiments were carried out for jet-to-mainstream density ratios of and Cited by: A quantitative measure of the strength of the pressure-velocity correlation of a Machaxisymmetric jet, with an exit nozzle diameter of mm is examined.

The exit flow temperature is held constant at a temperature of 25°C, and is pressure and temperature balanced with ambient by:   The local maximum jet velocity at P 1 and P 2 is approximately equal and is presented in Fig.

2.The maximum jet velocity in the corner could then be written as: (1) u m P 1 = u m P 2 In earlier studies, the separation distance in the corner can be expressed as: (2) Experimental investigation of temperature and velocity distribution about a rocket jet book x = L R e slot − 3 / 14 where s x is the jet separation distance along the ceiling, L is the distance from the slot jet.

In this part of the experimental investigation, the main stream and coolant were at the same temperature T ∞ = T c = 30 °C with the main stream Re ∞ = × 10 5. PIV images of the instantaneous scattering of the tracing particles are shown in the left column of Fig. The performance of a newly designed corner impinging jet air distribution method with an equilateral triangle cross section was evaluated experimentally and compared to that of two more traditional methods (mixing and displacement ventilation).

At nine evenly chosen positions with four standard vertical points, air velocity, turbulence intensity, temperature, and tracer gas decay measurements. Hartnett, J.

& Eckert, E. Experimental study of the velocity and temperature distribution in a high velocity vortex-type flow Trans. ASME. 79, Hilsch, R. Die Expansion von Gasen im Zentrifugalfeld als Kälteprozess Z. für Naturf. 1, Close Drawer Menu Close Drawer Menu Menu.

Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of. Experimental investigation of an axisymmetric free jet with an initially uniform velocity profile An experimental investigation was conducted to determine the flow characteristics of a circular free helium jet having an initially uniform velocity profile.

Complete velocity profiles are presented at Reynolds numbers of and at 0, 3, 6, 10, 15, and 20 nozzle diameters (where possible.

Solid Rocket Motor for Experimental Sounding Rockets Figure 4: Basic design of prototype motor. Nozzle Nozzle is the part responsible for production of thrust in a rocket motor; it increases the velocity of exhaust gases. A de Laval (convergent-divergent) nozzle with a. In the present study, an experimental investigation has been carried out to analyze the heat transfer characteristics of CuO–water nanofluids jet on a hot surface.

A rectangular stainless steel foil (AISI, mm thick) used as the test surface is electrically heated to obtain the required initial temperature ( °C).

Experimental data for the Mach jet were compared with the predictions of center-line velocity decay and jet spreading rate obtained by employing various formulations of eddy viscosity coefficient in an analysis similar to that of Warren.

SYMBOLS Measurements for this investigation are given first in the International System of. Maximum ceiling jet gas velocity in the steepest upward direction (m/s) “The Distribution of Temperature and Velocity Due to Fires Beneath Ceilings,” F.R.

NoteBuilding Research Establishment, “An Experimental Investigation of the Heat Transfer from a Buoyant Gas Plume to a Horizontal Ceiling—Part 2. The influence of injection conditions on rocket engine combustion stability is investigated for a sub-scale combustion chamber with shear coaxial injection elements and the propellant combination hydrogen–oxygen.

The experimental results presented are from a series of tests conducted at subcritical and supercritical pressures for oxygen and for both ambient and cryogenic temperature hydrogen. @article{osti_, title = {Experimental investigation on structures and velocity of liquid jets in a supersonic crossflow}, author = {Wang, Zhen-guo and Wu, Liyin and Li, Qinglian and Li, Chun and College of Aerospace and Engineering, National University of Defense Technology, Changsha }, abstractNote = {Particle image velocimetry was applied in the study focusing on the structure.

The present work aims to investigate the interaction between a plasma jet and targets with different physical properties. Electrical, morphological and fluid-dynamic characterizations were performed on a plasma jet impinging on metal, dielectric and liquid substrates by means of Intensified Charge-Coupled Device (ICCD) and high-speed Schlieren imaging techniques.

velocity decaying rates, turbulence intensity, etc become invariant. Despite voluminous research on basic statistical parameters, much lesser number of studies has compared experimental and modelling results.

In this study, we aim to investigate the flow dynamics of a plane jet at various jet-exit Reynolds numbers (Re h) given by Re / hb Uh (1) U b. On the new temperature scale, the temperature of a healthy person is degrees F.

Because there are degrees C and degrees F between the same reference conditions: 1 degree C = 1 degree F * / = 1 degree F * 5 / 9. The velocity at the exit of the nozzle of a typical laboratory jet has a smooth profile and a low turbulence level, about % - % of the mean velocity.

Due to the velocity difference between the jet and the ambient fluid, a thin shear layer is created. Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications.

The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging. The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves.

The detonation wave initiation in detonation tube in. where M is the rocket mass, Δv R is the increase in velocity of the rocket in a short time interval, Δt, m° is the rate of mass discharge in the exhaust, v e is the effective exhaust velocity (nearly equal to the jet velocity and taken relative to the rocket), and F is quantity m°v e is the propulsive force, or thrust, produced on the rocket by exhausting the propellant.

Because it is the main component of the air, it is convenient to use nitrogen and its molecular properties are known from room temperture to temperatures of about degrees Celsius from experimental measurements. Although this is a large range, it is far short of what is needed for some applications.

It has been shown that the jet velocity must be signiflcantly higher than the tangential velocity of the grinding wheel in order to penetrate the grinding wheel boundary layer and efiectively cool the arc of cut. To investigate the velocity distribution of a circular air jet at a number of stations along the length, to reveal how a uniform jet mixes with its surroundings by using StudentShare Our website is a unique platform where students can share their papers in a matter of giving an example of the work to be done.

conditions had been previously performed, and the gas temperature, velocity, composition, and flow direction were unknown. In the work reported herein, flow conditions near the injector were determined for a small heptane-liquid oxygen rocket engine.

The rocket. Experimental and numerical investigation of an axisymmetric freejet development of jet and shape of the mean velocity profiles. Profiles for Reynolds number of 16, were temperature mode. The mean velocity variations in the axial and radial directions have been measured using this probe.

The rocket leaves the barrel with low energy, and accelerates until the fuel is exhausted at about 60 feet (18 metres), at which point the grain rocket has a velocity of about feet per second ( m/s), slightly greater than Mach one, with about twice as much energy as the common ACP round.

Investigation on the mixing mechanism of single-jet film cooling with various blowing ratios based on hybrid thermal lattice Boltzmann method International Journal of Heat and Mass Transfer, Vol. 97 Full-Scale Turbine Vane Endwall Film-Cooling Effectiveness Distribution Using Pressure-Sensitive Paint Technique.

A simplified method has been developed by TEA Group and ENI E&P for the complete characterization of atmospheric blow-outs. The core of the method is a zero-dimensional model of well flow. velocity profile resembling a Gaussian curve that becomes wider and shorter with distance from the nozzle outlet.

In this region, the axial velocity and jet width vary linearly with axial position. Martin [2] provided a collection of equations for predicting the velocity in the free jet and decaying jet regions based on low Reynolds number flow.

A digital thermometer for measuring atmospheric temperature is located on the side of the open-jet tunnel next to the test section (see same Figure).

Temperature is read in degrees Celsius or Fahrenheit, depending on the thermometer setting. The gas constant Rin the equation of state for a perfect gas (p =ρRT) is J/kg/K. @RussellBorogove's answer mentions temperatures of roughly K and K in the combustion chamber and exhaust of a big rocket engine.

The canonical Wikipedia plot of velocity and temperature for a de Laval nozzle is shown below as a schematic representation only. Ignoring some aspects of gas theory, we can estimate the thermal velocity of a molecule using.

T = absolute temperature of inlet gas, K R = Universal gas law constant = J/(kmolK) My last question is the exhaust velocity of the rocket is its initial velocity or final velocity. I did a problem dealing with a rocket and I need it to find the velocity f of a rocket using the P i = P f formula.

Last edited: what is the speed of a jet plane that travels 3, meters in 10 seconds. m/sec. the dependent variable is a book rests on a table. the force of gravity pulls down on the book with a force of 20 newtons.

what prevents the book from accelerating downward at m/sec² a question. "how does adding salt affect the boiling temperature o. The relaxation of particle velocity and the relaxation of temperature have characteristic time scales, which should be compared to the time scale of.

Development of test stand for experimental investigation of chemical and physical phenomena in Liquid Rocket Engine J. Manag., São José dos Campos, Vol.3, No.2, pp. May-Aug., weaker when temperature is increased. Cooling, thus, reduces the wall temperatures to an acceptable value (Sutton, ).

The Scale of a Model Rocket X. X 22 Rocket Motion Video Studies. X 23 Predicting and Measuring Rocket Parachute Drift Rate. Rocket Parachute Flight Duration X.

Project Enterprise (2 weeks) X. X X. Legend: X: Denotes the primary target word focus (altitude, velocity and/or acceleration).: Denotes secondary target word. Velocity profile has a top-hat distribution initially, but attains a Gaussian shape at the end of the ZFE.

Flow in ZFEo oo o Qx x x D QD D ⎛⎞ =+ + ⎜⎜ ⎟⎟ ≤ ⎜⎝⎠ ⎟⎟ 2 1 0 0 6 2 (Albertson et al. ) Zone of Established Flow (ZEF) Extends from where the water entrained at the edges of the jet. an experimental study of vortex flow for application to gas-phase fission heating Technical Report Keyes, Jr., J.

J. ; Dial, R. E. An experimental investigation into the gas dynamics of a jet-driven vortex tube for application of a cavity nuclear reactor to rocket propulsion has shown that viscous retardation of the vortex motion is severe.Experimental investigation of the induction compressor has shown that the mathematical analysis presented earlier leads to correct prediction of the forces on a conductor.

The peristaltic operation assumed in the theory is not achieved because of simple hydrodynamic principles, which are discussed.0, and velocity v 2 of the stone (propellant) expelled, one is able to calculate from this equation the increased boat (rocket) velocity v 1.

Doing so, this equation affirms our daily experience that hurling the stone backward increases the speed of the boat, while doing it forward decreases its speed. Rocket Principles Momentum Thrust.