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Air Jet Experiment
Abstract
A plate with a spring gauge is placed at the Pitot tube probe and there is an entry called orifice and exit called nozzle for the air generated by a fan. The fan gives air flow which makes the pressure on the plate on the opposite direction of the gravity as a force. The force on the plate can be measured http://www.ukassignment.org/ygkczy/ in this experiment or calculated from the theory. Additionally the nozzle forms a jet boundary which is variable by the height of the plate. It was observed that the nozzle gives larger diameter of the boundary as the height of the plate increases. The force calculated in the theoretical work is larger than observed in the experiment.
The experimental problem and theory
The first experiment is to study the force of a plate impinged by an air jet. The second experiment is to study the formation of a round air jet by a nozzle, tested by a plate.
The force applied on the fluid with a certain length of time period has the result to change the momentum of the fluid. In other words, the force has the effect as the velocity change of the fluid at its mass flow rate.
Methodology
The first experiment is to measure the force on the round plate by jet below, for different distances.
The second experiment is to measure the effective area of a jet. In additional to the height of the plate is a variable, the radial distance is another one so that at large distance it will ultimately gives zero force.
The plate has a spring gauge so that the force on it can be measured. The plate can be placed above the nozzle and adjusted to different heights and redial distances. The pitot tube has a probe which connects the manometer. Fan gives air jet to the nozzle.
In experiments results are collected in trials which are compared with theoretical calculations.
Results and Discussion
For the first experiment plate heights from 0 to 90 cm are measured with step size 10 cm. From 0 to 90 cm the force measured are 1200g, 1080g, 1060g and so forth, respectively. In other words from 20 cm up the force remained in 1060g. The fan gives a pressure as 25mm fluid level increase was observed.
Pressure
P = 784* 9.8 * 0.025*sin15
Velocity at the orifice
v(d) = sqrt(2P/Rho(air))
Exit velocity
v(e) = v(d) * (70/25)^2 = 71.07
mass flow rate
Rate(m) = C(d)rho(air)v(e)A(e) = 0.6*1.21*v(e)*A(e)= 0.0253 kg/s
Air density used = 1.21 kg/m^3
Force on the plate can be derived as
F = rate(m)*v(e) = C(d)*rho(air)*v(e)^2*A(e) = 1.798 kg
This value is larger than the experiment observed, which is about 1.08, 1.06 kg.
For the second experiment heights from 0 to 80 cm with step size 10 cm are measured with each height has 8 trials in different distances from center http://www.ukassignment.org/ygkczy/ to outskirt. The measured fluid levels in manometer give that for closer distance to the nozzle, the central pressure is larger than further distance to the nozzle (i.e. lower position vs. higher position). On the other hand the boundary of the nozzle is increased as the plate was moved to higher (further) position. In other words, to develop nozzle area it needs a certain distance as the basis.
In experiment 2, the jet boundary can be approximated by average on the weighted sum of force at each height; weight is taken as the redial distance, hence
height weighted sum sum jet boundary
10 92 229 0.401747
20 108 169 0.639053
30 50 84 0.595238
40 90 75 1.2
50 93 57 1.631579
60 101 47 2.148936
70 100.5 39.5 2.544304
80 87.5 34 2.573529
Figure 1: The force as a function of the plate height
Figure 2: The average diameter as a function of the plate height.
Conclusions
It was observed that the nozzle gives larger diameter of the boundary as the height of the plate increases. The force calculated in the theoretical work is larger than observed in the experiment.
Compressible Flow Experiment
Abstract
Experience significant changes in the density of the fluid behavior are described compressible flow. Magnetic flux density can be simplified for analysis of flow behavior by assuming a constant density does not change significantly. This leads to the theory of idealized incompressible fluid. As a result, in most cases, significant changes in the density and gas, liquid handling (especially for high sales) because the flow of large pressure changes that can handle these cases, you can fix you must be obtained when analyzing the compressible flow.
The experimental problem and theory
The rest of the gas at supersonic speed in order to facilitate the convergence of the gas duct and the branch line for the first time subsonically accelerated by adding to the speed of the supersonic expansion is very important. Therefore, the outlet nozzle is designed to achieve supersonic flow conduit is convergentdivergent. Throat Mach number, can not exceed 1, the mass flow rate decreases, the output pressure of the nozzle becomes constant. This is the breath of the nozzle flow. Or equal to the formation of shocks, output does not exceed the design pressure or flow and shock wave deceleration nozzle pressure ratio that is designed to work are formed.
Methodology
Experiment 1: Resolving the change in pressure and counterpressure
(A) supply pressure valve and back pressure valve is fully opened, is all.
(B) such that the pressure re-measured static pressure probe completely surprised.
(C) by adjusting the pressure valve on the pressure 500 kPa, reading level
In order to measure;
(D) to adjust the pressure to change again to a new pressure valve: back of the stage pressure rise
Again, the pressure is the same procedure until the supply pressure. At each step, reading the water of the slope of the level of the pressure.
Experiment 2: the axis of the nozzle, the measurement of static pressure variation along the flow
In this experiment, the two must be made to the supply pressure P0. Each supply pressure
It must re-establish the pressure of your number. Some results of the election to cover the back
Regimes: (A) through the speed of sound, (B) Sonic subsonic (neck) supersonic subsonic shock
O (C) Sonic (design conditions) subsonic procedures in place at each step, reading the water level is the same as in Experiment 1, through exploration and reading the pressure at the nozzle through the nozzle gauge metric.
Results and Discussion
By adding a column to promote the cause of the fluid flowing through pipe sales in subsonic flow, it takes some time to add a column to a supersonic flow of a pipe flow. Zoning changes will make the flow of friction choking Mach number required to reach the column, similar to the above case will be added later.
For the ideal gas constant area of the pipe, the pipeline was held at Mach number of non-identical effects of changes in temperature is due to explain how you can use to calculate the Rayleigh flow model. Fixed temperature when the isentropic depression if it is delayed, in making liquid is the temperature. Increasing the temperature of the heat, such as congestion, added to the system.
Variation of mass flow rate with back pressure
back pressure Pb manometer water levels in inches p1-p2 mass flow rate
0 1.9 435.61 0.000351
50 1.9 435.61 0.000351
100 1.9 435.61 0.000351
150 1.85 423.164 0.000346
200 1.9 435.61 0.000351
250 1.9 435.61 0.000351
300 1.9 435.61 0.000351
350 1.85 423.164 0.000346
400 1.6 360.934 0.00032
450 0.85 174.244 0.000222
500 -0.1 N/A N/A
And additional variables are available given the changes in the density analysis. Generally, conservation of mass conservation equation for incompressible flow can be resolved by considering, as opposed to. In general, includes the principle of conservation of energy. However, this is another variable (temperature), and the fourth equation, therefore, to describe the thermodynamic temperature of the flow that is required (e.g., ideal gas equation of state, etc.) has been introduced.
The identity politics of the density of the fluid density isentropic you, ρ0, the reference value, when you define a way to compress the stream can are stopped if that helps you compare the density. In principle, the static density is 5% or more relative to the change in density, must be analyzed and then compress the fluid flow. Ideal gas specific heat at a rate of 1.4 cases around the Mach number is greater than 0.3 occur. Below this value, however, in certain cases, may depend heavily compressed or the level of accuracy required, should be treated likely.
T = 473(1/5)^(1-1/1.2) = 361.7K
delta(s)/R = ln(p1/p2)(t2/t1)^(gamma/(gamma-1))
delta(s)/R = ln5(361.7/472)^3.5 = 0.671
delta(s) = 192.5J/Kg*K
p2 = p1+ delta(p) = 125kPa
p2/p1 = (Ma^2(gamma-1)/2+1)^(gamma/(gamma-1))=125/105
Ma = 0.634
a=rRT^0.5 = (1.4*287*294.7)^0.5 = 343#p#分页标题#e#
u = 217.7 = a*Ma
a1 = sqrt(rRT) = sqrt(1.3*188.95*300) = 271.46
T2/T1 = (1+(gamma-1)*M1^2)/2)/(1+(gamma-1)*M2^2)/2)
T2 = 399
u2 = a2*M2 = 201
Theoretical computation of the maximum mass flow rate
A(throat) = 3.14159*0.00479^2/4 = 1.80202E-05
M(max) = A(throat)*(1.21*287*294.4*1.21*1.4*(5/6)^6)^0.5 = 0.004339863
Conclusions
One of the most common examples of shock waves of compressible flow phenomena. Impact on the thermodynamic properties is characterized by discontinuous change. Pressure wave is suddenly removed from the series together to form a membrane separating two different regions of compression or shock-dimensional flow. This is a technique used to generate shock waves in shock tube is often. Compressible fluid nozzle has an important role in determining behavior. Subsonic and supersonic flows react differently to changes in cross section. http://www.ukassignment.org/ygkczy/ Convergence of the duct (small diameter, large diameter in the direction of flow reduction) is increased through experience, the speed of subsonic flow, supersonic flow by reducing the speed of the train, making the production. In general, the flow through a convergent nozzle, the Mach 1 always tends to be. Convergence is large enough to reach the speed of sound, known as the place "choking" phenomenon. In this case, the flow of shortness of breath, and the two tubes at once, speed limits, number of shock Mach entering the fluid flow area or at least (and units like this is known as a sore throat maintenance, etc.), type of nozzle. Similarly, the difference between slow flow is always subsonic flow through a nozzle, and is supersonic.
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