first one

Saturday, 3 July 2021

Reynold's Experiment

REYNOLD’S EXPERIMENT

It was introduced by Osborne Reynolds (1842–1912), who popularized it’s use in 1883. In his 1883 paper Reynolds described the transition from laminar to turbulent flow in a classic experiment, in which he examined the behavior of water flow under different flow velocities using a small stream of dyed water introduced into the center of clear water flow in a larger pipe. The larger pipe was glass so the behavior of the layer of the dyed stream could be observed, and at the end of this pipe there was a flow control valve used to vary the water velocity inside the tube. When the velocity was low, the dyed layer remained distinct through the entire length of the large tube. When the velocity was increased, the layer broke up at a given point and diffused throughout the flu-id's area cross-section. The point which this happened was the transition point from laminar to turbulent flow. The ratio of inertia forces to viscous forces, the parameter obtained is called the Reynolds number (Re), in honor of Osborne Reynolds

where,
Re = Reynold’s number
V = velocity of fluid
D = diameter of pipe
μ = dynamic viscosity of fluid
ρ = density
With respect to Reynolds number: Re = 2300 transitional flow.

Laminar Flow (Re < 2300, only in pipe): Laminar flow may be described as an orderly pattern , i.e. in laminar flow the fluid moves in layer, or laminas, one layer sliding over an adjacent layer with only a molecular interchange of momentum. Such that the transverse exchange of momentum is insignificant.

Turbulent Flow (Re > 2300, only in pipe): The turbulent flow is a three-dimensional random phenomenon, exhibiting multiplicity of scales, possessing

HYPERSONIC FLOW

hypersonic flow

Flow streams with Mach number about 5 are generally termed HYPERSONIC. What is scared about Mach number 5? Is the upper limit for hypersonic flow finite or infinite?. The Mach number 5 is treated as the lower limit of Hypersonic flow. This is because up to Mach number 5, any change in flow velocity is dictated by the change in flow velocity as well as the change in the speed of sound. In the accel-erating supersonic flow, the change in magnitude of absolute velocity is more than the change in speed of sound. But for accelerating Hypersonic flow, the change in flow Mach number is dominated by the change in speed of sound and the flow ve-locity is not dominant. For example, for increase of Mach number from 5 to 7, the decrease of speed of sound is predominant compared to increase of flow velocity. In other words, it may be stated that for Mach numbers above 5 the effect of change in speed of sound Hypes the change in flow Mach number (the sonic effect dictates the Mach number change or the sonic effect Hype the Mach number change) and hence the flow is referred to as HYPERSONIC. The upper limit for Mach number of hypersonic flow is around 40. Flow with Mach number above 40 would experience very strong tempera-ture effects, leading to dissociation and ionization and field is referred to as high enthalpy gas dynamics, which encom-passes high-temperature and plasma flows.

Reference: Rathakrishnan. E, Gas Dynamics, Seventh Edition, Prentice Hall of India Pvt. Ltd, New Delhi, 2020

SOUND BARRIER

Sound Barrier

Sound barrier means the increase in aerodynamic drag as an airplane approaches the speed of sound. In the air, the speed that the waves travel is determined by atmospheric conditions, so the speed of sound can vary depending on temperature. The sound barrier is a concept developed in the early 20th century, when many scientists believed that the drag on aircraft caused by approaching the speed of sound made it impossible for any aircraft to reach or exceed the speed of sound without being destroyed. Most of the time, it isn't even noticeable. Breaking the sound barrier is usually something for military aircraft, as few commercial aircraft have top speeds over the speed of sound. Flying faster than sound produces a sonic boom.

In 1942, the United Kingdom's Ministry of Aviation began a top-secret project to develop the world's first aircraft capable of breaking the sound barrier. The project resulted in the development of the prototype Miles M.52 turbojet-powered aircraft, which was designed to reach 1,000 mph (417 m/s; 1,600 km/h) (over twice the existing speed record) in level flight, and to climb to an altitude of 36,000 ft (11 km) in 1 minute 30 seconds.

Friday, 25 June 2021

ION TRANSPORT MEMBRANE TECHNOLOGY

 

ION TRANSPORT MEMBRANE TECHNOLOGY(ITM)

Ion transport membrane (ITM) technology is a key perspective for efficient oxygen separation. At the present time, semi-industrial modules based on ceramic ITMs produce oxygen of 98.9%–99.9% purity. In order to improve the oxygen purity, using newly developed liquid-oxide ITMs along with the highest oxygen selectivity, these membranes exhibit competitive oxygen permeability and could be successfully used for ultrahigh purity oxygen separation. Oxygen is the second-largest volume industrial gas that has numerous applications in aerospace, metallurgy, power engineering, environmental, medicine, etc. Ultrahigh purity oxygen (>99.999% purity) is in demand in the solar, semiconductor, chemical, and pharmaceutical industries. Recently, renewable sources of energy (sun, wind, biomass, etc.) are rapidly gaining in popularity. Clean energy, especially photovoltaics (PV), is a field of major growth and investments.

 Oxygen is one of the ultrahigh-purity process gases needed by the PV cell manufacturing. At the present time, ultrahigh purity oxygen is produced by water electrolysis or distillation method. However, these method-based oxygen production technologies are energy-intensive. In recent decades, energy-efficient ion transport membrane (ITM) technology is developing to produce pure oxygen. Conventional ITMs are the ceramic membranes with high oxygen ion conduction at elevated temperatures. There are two ITM processes. In the first, a mixed ionic electronic conducting (MIEC) membrane operates with a difference of the oxygen partial pressures, as illustrated in Fig. 1a. Under the oxygen electrochemical potential gradient, ambipolar conductivity of ions and electrons provides a sufficient oxygen permeation flux through the MIEC membrane. The MIEC membrane-based separation process is referred to as ITM oxygen. In the second process, an ion-conducting membrane (or an electrolyte) operates with a voltage.

In contrast to the first process, electron transfer occurs in the outer circuit, as illustrated in Fig. 1b. Devices utilizing electrolytes are referred to as oxygen generators. The envisioned ITM applications vary from the generation of pure oxygen and partial oxidation of methane (membrane reactors for syngas production) to the capture of CO2 in oxy-fuel power plants. Oxygen permeation flux through MIEC membrane is limited by diffusion. Therefore, the minimization of membrane thickness is necessary to achieve a high oxygen permeation flux. However, the brittle thin-film ceramic membrane material has a very low mechanical strength. As a rule, a thin membrane film is deposited on a porous support (it is so-called asymmetric membrane). To provide the thermochemical compatibility between membrane and support, they are usually made of the same material. The surface exchange reaction rates can limit the oxygen permeation flux through a thin MIEC membrane. An appropriate catalyst is deposited on the membrane to increase the rate of surface exchange reactions. Gas transport in a porous support can also control the oxygen permeation flux through asymmetric membranes. In order to ensure the sustainable production of oxygen, numerous asymmetric membranes with high oxygen permeability have been developed. Currently, asymmetric membrane-based semi-industrial modules produce oxygen of 98.9%–99.9% purity.

Three types of liquid-oxide ITM materials have been developed: (i) mixed ionic electronic conducting (MIEC), (ii) bilayer mixed ionic electronic conducting—redox (MIEC-Redox) and (iii) ionic conducting (electrolytes). In contrast to the MIEC and ionic conducting membrane materials (Figs. 1a and 1b), the bilayer MIEC-Redox membrane materials have a combined diffusion bubbling oxygen mass transfer. The chemical diffusion of oxygen takes place in the external layer of the membrane material, while in the internal layer, the redox reactions and nucleation, growth and transport of oxygen gas bubbles occur, as illustrated in Fig. 1c. The concept of highly selective liquid-oxide ITMs opens up ample opportunities for oxygen separation technology. However, in order to realize the potential of these membranes and successfully commercialize them, many scientific and technical challenges remain to be solved.

The rare earth stabilized bismuth oxide and rare-earth doped ceria are usually used as the oxygen generator electrolytes. To achieve a sufficient ionic conductivity of these electrolytes, oxygen generators operate in the temperature range of 700 °C–800 °C. The purity of oxygen produced by the ceramic electrolyte depends on the electrolyte density. At the present time, the product grades of 98%–99.99% oxygen are available.

Monday, 20 April 2020

AEROFOIL THEORY

Every theory will contain some assumptions and some basic tools required.Here those basic tools will be discussed.

>>Primarily consider the surface of the aerofoil is with vortex completely and this is applicable for
only thin aerofoil.

>>FOr thin aerofoil to formulate flow characteristics over the aerofoil are obtained as follows:
 
     *On the surface of the aerofoil i.e upper and lower surfaces,simple vortex is assumed everywhere.
     *If aerofoil is viewed from for away distance it appears to fall on chord  or chamberline.
     *Hence is assumed that to analysing flow characteristics over aerofoil simple vortex on the chord
or chamberline.

BASIC TOOLS:

>> Consider a simple vortex at point "o" with strength  Г .
>> Imagie a straight line passing through origin "o".
      and the straight line is etended to the -∞ to +∞ .
 >>Infinite number of simple vortex on the straight line to be imagined.
>>Call the line as the straight vortex filament and strength of the vortex filament is  Г as the simple
vortex.
>>The straight vortex filament induces a velocity and imagine infinite number of straight vorte filaments.
>>The side by side vortex filaments also forms straight vortex sheet. 
>>The strength of each straight vortex filament is very small.
>>Consider the edge view of the vortex sheet we obtain a curve line in XZ-plane.
>>Since it is a continues portion of the sheet taking up the distance measured from a to b is S.
>>Consider a small distance ds. ४ is the strength of the vortex line sheet per unit length.
           strength of the vortex sheet of length   ds=४.ds
>>The strength of entire vortex sheet=Г.
                                  
>>Consider a point P in the element distance 'r'. r is the distance from the point p to the element vortex sheet.
>>The velocity induced at elemental vortex sheet will be as dv is the velocity induced by elemental vortex sheet.
                                                           dv=(-४.ds)/2πr.
>>Consider elemental size of vortex sheet of ds.Length in a rectangle box.
>>Circulation around the rectangular box or closed path.
४=(u1-u2)
>>It states that local jump in tangential velocity across the vortex sheet equal to the local strength of the sheet with the given length.

KUTTA condition:

>>Actual airfoil trailing edge is having a finite angle.In theoritical aerofoil the upper surface and lower surface will form a point.
>>Velocity along the upper surface and lower surface is v1 and v2. v1 is parallel to upper surface at point a. v2 is parallel to lower surface at point a.
>>For the finite angle trailing edge it appears that at point a. we will have two different velocities in two different direction.
>>It is not physically possible if v1 and v2 are finite.only possible when v1=v2=0.
>>For the finite angle trailing edge point a trailing edge is a stagnation point.
>>For theoritical aerofoil v1=v2=0.since direction is same.

summary:

>>For a given aerofoil at a give angle of attack the value of  ४  around aerofoil is such that the flow leaves the trailing edge smoothly.
>>If the trailing edge is a finite angle,trailing edge is the stagnation point.
>>If the trailing edge is the cuspid then the velocities leaving the top and bottom surface are finite and equal in magnitude and direction.

Thursday, 16 April 2020

POTENTIAL FLOW THEORY

INTRODUCTION:

This particular flow is a ideal flow which is not a real flow.This particular flow may not be there in physically possible flows due to viscosity.we consider potential flow as the non-viscous flow i.e neglecting viscosity.This potential flow will help us to understand the lift force on an object.But doesn't talk about the drag force.


continuity equation:

       velocity vector⇒ v=uî+vĴ
       then,
              ටu/ ටx   +   ටv/ ටy  = 0
             This is the continuity equation.
*The velocity vectors which satisfies the above equation such flow fields are physically possible flow  fields.That particular flow field will have a stream function (ψ) or else no streamm function.

Irrotationality:

   Rotational means rotating itself on its own axis.not rotating about a common axis.
              ටv/ ටx   -  ටu/ ටy  = 0
            This is irrotationality condition.

 DERIVATION FOR POTENTIAL FLOW EQUATIONS:

>>stream line is a mathematical line which flow velocity is tangential.
eq of stream line:
         udy -vdx =0
     
    u= ටψ/ටy      v=  - ටψ/ටx

   tanθ=dy/dx   =v/u.

eq of stream line:
>> udy -vdx =0
>>(ටψ/ටy)dy  -  (- ටψ/ටx)dx =0
>> (ටψ/ටx)dx + (ටψ/ටy)dy =0
      This is the total derivative of  ψ.
>>d ψ=0
      integrating on both sides
>> ψ=const.

*This says that along any stram line, stream function is constant.
*Another point is no two stream lines have the same stream function  ψ.

From  irrotationality condition:
>>  ටv/ ටx   -  ටu/ ටy  = 0
>>ට(ටФ/ටy)/ ටx   -  ට(ටФ/ටx)/ ටy  = 0

*If a flow field is possible and irrotational it can have only  ψ.
*If the flow field is not possible and irrotational it can have Ф.
*suppose the flow field is possible,irrotational such flow field can be represented by ψ and Ф.

equations of potential flow:

If any flow have ψ and Ф.Then,it is called potential flow and it satisfies the below equations



and

   Фxx +Фyy =0.