1) A normal shock wave occurs when the flow velocity decreases abruptly from supersonic to subsonic speeds. Flow properties like pressure, temperature, and density change discontinuously across the shock.
2) The flow Mach number decreases from a value greater than 1 upstream to less than 1 downstream. Pressure and temperature increase across the normal shock.
3) Normal shock waves are analyzed using the Rankine-Hugoniot equations which relate flow properties on both sides of the shock based on conservation of mass, momentum, and energy. Examples show how to calculate post-shock properties given pre-shock conditions.
Calibrating a CFD canopy model with the EC1 vertical profiles of mean wind sp...Stephane Meteodyn
For some projects, applying the basic rules of EC1 is not sufficient, and it is required to get a more accurate estimation of the wind speed on the construction site. This can be done by using computational fluid dynamics codes which have the advantage, both to take into account of the terrain inhomogeneity and to calculate 3D orographic effects. In this way, the orography and roughness effects are coupled as they are in the real world. However, applying CFD computations must be in coherence with EC1 code. Then it is necessary to calibrate the ground friction for low roughness terrains as well as the drag force and turbulence production in case of high roughness lengths due to the presence of a canopy (forests or built areas). That is the condition for such methods to be commonly used and agreed by Building Control Officers. In this mind, TopoWind has been developed especially for wind design applications and can be a very useful, practical and objective tool for wind design engineers. The canopy model implemented in TopoWind has been calibrated in order to get the mean wind and turbulence profiles as defined in the EC1 for standard terrains. In this way, TopoWind computations satisfy the continuity between the EC1 values for homogeneous terrains and the more complex cases involving inhomogeneous roughness or orographic effects
Calibrating a CFD canopy model with the EC1 vertical profiles of mean wind sp...Stephane Meteodyn
For some projects, applying the basic rules of EC1 is not sufficient, and it is required to get a more accurate estimation of the wind speed on the construction site. This can be done by using computational fluid dynamics codes which have the advantage, both to take into account of the terrain inhomogeneity and to calculate 3D orographic effects. In this way, the orography and roughness effects are coupled as they are in the real world. However, applying CFD computations must be in coherence with EC1 code. Then it is necessary to calibrate the ground friction for low roughness terrains as well as the drag force and turbulence production in case of high roughness lengths due to the presence of a canopy (forests or built areas). That is the condition for such methods to be commonly used and agreed by Building Control Officers. In this mind, TopoWind has been developed especially for wind design applications and can be a very useful, practical and objective tool for wind design engineers. The canopy model implemented in TopoWind has been calibrated in order to get the mean wind and turbulence profiles as defined in the EC1 for standard terrains. In this way, TopoWind computations satisfy the continuity between the EC1 values for homogeneous terrains and the more complex cases involving inhomogeneous roughness or orographic effects
Aerodynamics Part I of 3 describes aerodynamics of wings and bodies in subsonic flight.
For comments please contact me at solo.hermelin@gmail.com.
For more presentations on different subjects visit my website at http://www.solohermelin.com.
This presentation had been prepared for the aircraft propulsion class to my undergraduate and graduate students at Kasetsart University and Chulalongkorn University - Bangkok, Thailand.
Student information management system project report ii.pdfKamal Acharya
Our project explains about the student management. This project mainly explains the various actions related to student details. This project shows some ease in adding, editing and deleting the student details. It also provides a less time consuming process for viewing, adding, editing and deleting the marks of the students.
Aerodynamics Part I of 3 describes aerodynamics of wings and bodies in subsonic flight.
For comments please contact me at solo.hermelin@gmail.com.
For more presentations on different subjects visit my website at http://www.solohermelin.com.
This presentation had been prepared for the aircraft propulsion class to my undergraduate and graduate students at Kasetsart University and Chulalongkorn University - Bangkok, Thailand.
Student information management system project report ii.pdfKamal Acharya
Our project explains about the student management. This project mainly explains the various actions related to student details. This project shows some ease in adding, editing and deleting the student details. It also provides a less time consuming process for viewing, adding, editing and deleting the marks of the students.
About
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
• Remote control: Parallel or serial interface.
• Compatible with MAFI CCR system.
• Compatible with IDM8000 CCR.
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
• Easy in configuration using DIP switches.
Technical Specifications
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
Key Features
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
• Remote control: Parallel or serial interface
• Compatible with MAFI CCR system
• Copatiable with IDM8000 CCR
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
Application
• Remote control: Parallel or serial interface.
• Compatible with MAFI CCR system.
• Compatible with IDM8000 CCR.
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
• Easy in configuration using DIP switches.
Explore the innovative world of trenchless pipe repair with our comprehensive guide, "The Benefits and Techniques of Trenchless Pipe Repair." This document delves into the modern methods of repairing underground pipes without the need for extensive excavation, highlighting the numerous advantages and the latest techniques used in the industry.
Learn about the cost savings, reduced environmental impact, and minimal disruption associated with trenchless technology. Discover detailed explanations of popular techniques such as pipe bursting, cured-in-place pipe (CIPP) lining, and directional drilling. Understand how these methods can be applied to various types of infrastructure, from residential plumbing to large-scale municipal systems.
Ideal for homeowners, contractors, engineers, and anyone interested in modern plumbing solutions, this guide provides valuable insights into why trenchless pipe repair is becoming the preferred choice for pipe rehabilitation. Stay informed about the latest advancements and best practices in the field.
Water scarcity is the lack of fresh water resources to meet the standard water demand. There are two type of water scarcity. One is physical. The other is economic water scarcity.
CFD Simulation of By-pass Flow in a HRSG module by R&R Consult.pptxR&R Consult
CFD analysis is incredibly effective at solving mysteries and improving the performance of complex systems!
Here's a great example: At a large natural gas-fired power plant, where they use waste heat to generate steam and energy, they were puzzled that their boiler wasn't producing as much steam as expected.
R&R and Tetra Engineering Group Inc. were asked to solve the issue with reduced steam production.
An inspection had shown that a significant amount of hot flue gas was bypassing the boiler tubes, where the heat was supposed to be transferred.
R&R Consult conducted a CFD analysis, which revealed that 6.3% of the flue gas was bypassing the boiler tubes without transferring heat. The analysis also showed that the flue gas was instead being directed along the sides of the boiler and between the modules that were supposed to capture the heat. This was the cause of the reduced performance.
Based on our results, Tetra Engineering installed covering plates to reduce the bypass flow. This improved the boiler's performance and increased electricity production.
It is always satisfying when we can help solve complex challenges like this. Do your systems also need a check-up or optimization? Give us a call!
Work done in cooperation with James Malloy and David Moelling from Tetra Engineering.
More examples of our work https://www.r-r-consult.dk/en/cases-en/
Final project report on grocery store management system..pdfKamal Acharya
In today’s fast-changing business environment, it’s extremely important to be able to respond to client needs in the most effective and timely manner. If your customers wish to see your business online and have instant access to your products or services.
Online Grocery Store is an e-commerce website, which retails various grocery products. This project allows viewing various products available enables registered users to purchase desired products instantly using Paytm, UPI payment processor (Instant Pay) and also can place order by using Cash on Delivery (Pay Later) option. This project provides an easy access to Administrators and Managers to view orders placed using Pay Later and Instant Pay options.
In order to develop an e-commerce website, a number of Technologies must be studied and understood. These include multi-tiered architecture, server and client-side scripting techniques, implementation technologies, programming language (such as PHP, HTML, CSS, JavaScript) and MySQL relational databases. This is a project with the objective to develop a basic website where a consumer is provided with a shopping cart website and also to know about the technologies used to develop such a website.
This document will discuss each of the underlying technologies to create and implement an e- commerce website.
4. Special phenomenon associated with Comp Fluid Flow
1
(sin )
Mach Angle
M
α
When body is stationery
In case of Supersonic (M>1)
Zone of action
Zone of silence
5. Determine the velocity of a bullet fired in the air if the Mach angle is observed to
be 300 . Given that the temperature of the air is 22 0C, density 1.2 kg/m3, ϒ = 1.4
R = 287.4 J/kg K.
Ans: C = 344.6 m/s, U = 2481 km/hr
An observer on the ground hears the sonic boom of a plane 15 km above when
The plane has gone 20 km ahead of him. Estimate the speed of flight of the plane.
Ans: M = 1.67
Calculate the velocity and Mach No of a supersonic aircraft flying at an altitude of
1000 m where the temperature is 280 0K. Sound of the aircraft is heard 2.15 sec
After the passage of aircraft an the head of on observer. Take ϒ = 1.4, R = 287.4 J/kg K.
Ans: V= 488.68 m/sec, M = 1.45
15 KM
20 KM
6. Effect of Area variation on flow properties in Isentropic Flow
By continuity equation tan
AV cons t
Take natural log of both side
ln ln ln ln
A V C
On Differentiation
0
d dA dV
A V
So dA d dV
A V
By Euler Equation: 0
dp
VdV
(A)
7. 2
dV dp
V V
Or
By equation (A)
2
dA d dp
A V
2
2
1
dA dp d
V
A V dp
Or
2
2 2
1
dA dp V
A V C
2
2
1
dA dp
M
A V
2
1
dA dV
M
A V
So Since
dp
c
d
V
M
C
Since
2
dV dp
V V
Since
Effect of Area variation on flow properties in Isentropic Flow cont..
8. Effect of Area variation on flow properties in Isentropic Flow cont..
9. Stagnation and Sonic Properties
2
0
1
2
h h V
Stagnation enthalpy (ho) is given by
We knew that h = CpT
So
Hence,
2
0
1
2
p p
C T C T V
2
2
0 1 1
1 1
2 2
p
T V
V
T TC RT
Or 2
0 1
1
2
T
M
T
Since Cp = ϒR/(ϒ-1)
Similarly 1 1
2
0 0 1
1
2
p T
M
p T
1 1
1 1
2
0 0 1
1
2
T
M
T
h
T
p
ρ
h0
T0
p0
ρ0
10. Stagnation and Sonic Properties contt.
There is another set of condition where the flow is sonic i.e. M=1
These Sonic or Critical properties are denoted by asterisks: p*, T* etc
2
0
1
2
p p
C T C T V
We know that
1/2
0
2
1
R
V T T
or
Max velocity is given by
1/2
max 0
2
1
R
V T
At M = 1, we can write the previous equations as
0 1
2
T
T
1
0 1
2
p
p
1
1
0 1
2
11. An aeroplane is flying at 1000 km/hr through still air having a pressure of 78.5 kN/m2
(abs) and temperature -8 0C. Calculate on the stagnation point on the nose of the
Plane: Stagnation Pressure, Stag. Temperature and Stag. density. . Take for air =
R = 287 J/kg K and ϒ = 1.4.
Ans: p0 = 126.1 kN/m2, T0 = 30.4 0C, ρ0 = 1.448 kg/m3
Air has a velocity of 1000 km/hr at a pressure of 9.81 kN/m2 vacuum and a temp of
47 oC. Compute its stagnation properties and the local Mach No. Take atm air =
98.1 kN/m2, R = 287 J/kg K and ϒ = 1.4.
Ans: p0 = 131.3 kN/m2, T0 = 85.4 0C, ρ0 = 1.276 kg/m3
12. Normal Shock
•For supersonic flow in a passage or around a body, the downstream pressure and
Geometrical conditions may require an abrupt reduction of velocity and consequent
changes of the flow properties.
•A shock is then said to be occurred.
•Shock waves are highly localized irreversibility's In the flow. Shock formation is
possible for confined as well as for external flows.
•Normal shocks are substantially perpendicular to the flow and oblique shocks are
inclined at other angles.
13.
14. Flow Properties Across a Normal Shock
1 2
A1
P1
T1
M1
A2
P2
T2
M2
Normal
Shock
2
1
2
2
1 2
1
1
M
p
p M
2
1
2
2
1 2
1 1 2
1 1 2
M
T
T M
Mach No of a normal shock wave is always greater than
Unity in the upstream and less than Unity in the downstream.
2
1
2
2 2
1
1 2
2 1
M
M
M
Shock strength is defined by:
2
2 1
1
1
2
1
1
p p
Shock Strength M
p
2
1
2
2
1 1
1
1 2
M
M
Rankine – Hugoniot Equations
15. Calculate the downstream Mach No, pressure, temperature and shock strength of a
Normal shock wave observed to occur in an air nozzle at
M1 = 2, p1 = 20 kN/m2, T1 = 300 K
Ans: p2 = 90 kN/m2, M2 = 0.575, T2 = 510 K, Shock strength = 3.5
For a normal shock wave in air, Mach No is 2. If the atmospheric pressure and air
Density are 26.5 kN/m2 and 0.413 kg/m3 respectively, determine the flow conditions
Before and after the shock wave. Take ϒ = 1.4.
Ans: M2 = 0.577, p2 = 119.25 kN/m2, ρ2 = 1.101 kg/m3, T1 = -49.4 0C
T2 = 104.3 0C, V1 = 599.4 m/s, V2 = 224.6 m/s
16. Conclusion from 1D analysis of a Normal Shock:
• A normal shock can occur only if M1 >1
• M2 must be less than 1 for a normal shock
• Entropy rise across a shock increases
• p2/p1 and T2/T1 increases with M1