Show all your steps12R=1.8 mm,R2Thickness "8 =R2R1= 3.6 mm,RIVelocity = 4.36 m/s,klgenL= 100 mmAir Properties:kait= 0.0263 W/m.K.Vaik=15.89 x 10 m²/s, Pr= 0,707k = 1.23 W/m. K.Air (Too= 25) passes at velocity. V m/s in across flow around the rod. The outer surfacetemperature, T2=132° Heat is generated in a red (R1 kl = 4 w/m K), according toquen (r)"W/m²"R90 constant value1 What is temperature distribution inside the rod in-terms of heat generation: qo.surface temperature. T1, thermal conductivity: kl2. What is the convectrve heat transfer coefficient (W m2 K) at R2, heat transfer rate(W), the temperature at the Tod surface. T1"C the heat generation constant , qaWm3 and the maximum temperature in the fod C#SolutionTemperature distribution, in final formT(r)Convective heat transfer coefficient(W/m.K)Heat transfer rate=(W)T1=The heat generation constant, ɖo=(W/m)Immax°CShow nand written work below be clear, Step by step111111

1rddr(dTdr) + qgenk = 0 … (steady state) qgen = - k…

Answered: Show all your steps k2 R=1.8 mm, R2…

Show all your steps k2 R=1.8 mm, R2 Thickness “8" =R2 R= 3.6 mm, RT Velocity = 4.36 m/s, kl gen L= 100 mm Air Properties: 111111

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Related questions

Q: An airfoil section is being tested in a wind tunnel. The freestream properties are: velocity = 160…

Q: In an experimental set-up to measure the shock losses due to sudden expansion, the following…

Q: Corection the following number k=.02625,Kinematic viscosity(fancy v)=16.55*10^-6m^2/s,Pr=.7…

Q: Write the name of the table in the picture. Name the Appendix

Q: A normal shock wave propagates into atmosphere where the atmospheric temperature is equal to T₁ =…

A: please refer handwritten solution

Q: Problem 3: Smoke and Steam One of the most enduring images of the Industrial Revolution is a steam…

Q: Air flows over a flat plate at 38 m/s, 25°C and 1 atm pressure. The kinematic viscosity of air at…

A: Velocity of air , v=38 m/sTemperature of air, T=25o CPressure of air, P=1 atmkinematic viscosity,…

Q: 2. In an undistur bed airstream, where the pressure is 14.7 in' anɑ the remperature js 519 'R, the…

Q: a) Estimate the drag force on the plate. You may use the expression ?? = ∫ τ?dA b) When the flow…

A: Given Data: Water flows past a flat plate Plate Length L=5 m Plate Width w=2 m shear stress at the…

Q: Consider a slender body of revolution at zero angle of attack in supersonic flow with M.. = 3.0 as…

Q: A perfectly stirred cylindrical tank (D -2 m, H= 1.6 m) with steam jacket, is initially full of a…

A: Given data Aperfectly stirred cylindrical tank (0-2 m, H=1,6 m) with steam jacket, is initially…

Q: Problem 3: Aerodynamics Consider a UPS delivery van. Part A Is this vehicle streamlined? (yes/no)…

Q: 1- Calculate the pressure, temperature and velocity prior to the shock wave. 2- Determine if the…

Q: T z =? air oil A 2 of 2 2' ✓ s = 3.05 h =?

Q: Question one 2.2 takes a compression turn of 12°and then another turn of angle 0 in Figure. What is…

A: The ratio of flow velocity after a specific limit of sound speed is known as the Mach number. It is…

Q: Experimental measurements of the convection heat transfer coefficient for a square bar in cross flow…

Q: Instructions: 1. Clearly show your steps including formulas used in the calculation; 2. Show units…

A: To find: The shear stress, the required force and the Reynolds number. Given: Area of upper plate, A…

Q: Air at 20°C forms a boundary layer near a solid wall, in which the velocity profile, U = Umax sin TY…

Q: 23) Consider a rectangular hot plate shown below. U₁ = 3 m/s T₁ = 25°C Tb = 80°C Kin=200 W/mK Kair=…

A: V = 0.00002[m^3] " Maximum volume of fin" b_min = 1/1000000[m] "Minimum Gap between the fins" W =…

Q: Q1: Find the boundary layer thickness (8) equation, the shear stress (to) and the coefficient of…

Q: An aircraft has span efficiency factor = 0.7831, minimum drag coefficient = 0.025, wing area = 175…

Q: Question 4 In this open question, you are asked to propose a concept design and analyse a simple…

A: (b) (i) Air Conditions at the Inlet/Intake to the Wind Tunnel: For this proposed wind tunnel, the…

Q: The next figure shows a symmetric two dimensional wedge of half angle of 15°: If the wedge is well…

A: Given: M1 = 3.5 T1 = 20 + 273 = 293K

Q: T, = 25°C, U = 1.0m/s Known: Electric current passes through a thin flat foil heater A=0.25m? with…

Q: 2) A critical flow nozzle with a throat diameter of 5 mm is used to measure the flow of air. Air…

Q: - R1 = 7.6 mm - Thickness "S" k2 R2 Air R1 =R2-R1=3.6 - velocity V= 8.82 m/s V= m/s kl Igen L= 158…

Q: exhaust= Fluid leaves 400°C @34 mPa Bojter Tui bine I Pump efficieney= 0.80 = 80"/- Info: broiler…

A: Given data Turbine inlet conditions are : 4 MPa and 400°CTurbine exhaust conditions are : 10 kPaPump…

Q: [LO-1] Refer to the figure shown here and consider the data shown below: Oil Upper Plate F, v Lower…

Q: A steam generator generates flue gas at an average temperature of 260 C inside a Chimney. The…

A: Given DataP=100kPaV=10m/s[taken]T=26°CM=32Ta=21°Cm=15kg[weight of flue gas taken]

Q: HW 2 A 35 cm diam Suspended by a

A: The free-body diagram is as follows-

Q: Find the difference between the pressure ? PA- P, = ? TAKE // h = 2 m , h2 = 4 m, h 3m (Pwater =…

A: Given data:

Q: Problem 2: Professor Soma's 1/25,000h scale model measurement data showed that the maximum mixing…

A: Data given- Scale s = 1/25000 Maximum mixing length = 4 cm Maximum downward velocity = 1 m/s…

Q: "in' and the 2. In an undistur bed airstream, where the pressure is 14.7 semperature is 519 R the…

Q: M = 3.0 60 A = 40° ة و 6 = 20°

Q: Calculate the Reynolds numbers at the root chord location for the following aircraft. Assume that…

Q: 1. Consider a new wind tunnel to test and utilise the effects of boundary layer conditions in order…

Q: y = 1.4 M = 3.0 % $ = 40° 0 ts=20°

Q: Example :- Calculate the power in W/m3 required for mixing an oil of relative density 0.93 and…

Q: Example 2 Which of the two aircrafts in the figure flies at a supersonic speed? Air 220 K V = 320…

A: According to the information given, both airplanes are traveling at the same speed of 320 m/s. The…

Q: (Modeling/similarity) The pressure drop per unit length in a 0.286-in.-diameter gasoline fuel line…

A: From given data, similitude analysis has to be performed for internal flow (that is flow through…

Q: Q4//A// What are the advantages of: reheater, economizer, fixed row of steam turbine.

A: The purpose of all these process/ equipments like reheating, economizer, regenration, row of steam…

Q: Air at a temperature of 27°C (P = 1 atm) and a velocity of 12.7 m/sec flows over the top of a flat…

Concept explainers

Fluid Dynamics

The study of the flow of gases and liquids, usually in and around solid surfaces, is known as fluid dynamics in physics and engineering. Fluid dynamics, for example, can be used to evaluate the movement of air through an airplane wing or the surface of a vehicle. It can also be used in ship design to increase the speed at which ships pass through water.

Question

Show all your steps
12
R=1.8 mm,
R2
Thickness "8 =R2R1= 3.6 mm,
RI
Velocity = 4.36 m/s,
kl
gen
L= 100 mm
Air Properties:
kait= 0.0263 W/m.K.
Vaik=15.89 x 10 m²/s, Pr= 0,707
k = 1.23 W/m. K.
Air (Too= 25) passes at velocity. V m/s in across flow around the rod. The outer surface
temperature, T2=132° Heat is generated in a red (R1 kl = 4 w/m K), according to
quen (r)
"W/m²"
R
90 constant value
1 What is temperature distribution inside the rod in-terms of heat generation: qo.
surface temperature. T1, thermal conductivity: kl
2. What is the convectrve heat transfer coefficient (W m2 K) at R2, heat transfer rate
(W), the temperature at the Tod surface. T1"C the heat generation constant , qa
Wm3 and the maximum temperature in the fod C#
Solution
Temperature distribution, in final form
T(r)
Convective heat transfer coefficient
(W/m.K)
Heat transfer rate=
(W)
T1=
The heat generation constant, ɖo=
(W/m)
Immax
°C
Show nand written work below be clear, Step by step
111111

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

SEE SOLUTION Check out a sample Q&A here

Step 1

VIEW

Step 2

VIEW

Step by step

Solved in 2 steps

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

Show every step please not Ai generated im trying to understand what im doing wrong.
Three types of pin fins. The fins will be subjected to a gas in cross flow at v= 10 m/s. The cylindrical fin has a diameter of D = 20 mm, and cross-sectional area is the same for each configuration shown in the sketch. D V, Т. V, T. V, T Configuration A Configuration B Configuration C For fins of equal length and therefore equal mass, which fin has largest heat transfer rate? Assume the gas properties are those at T (treat it as air) = 350 K. Hint: Assume the fin can be treated as infinitely long.
Please help me get the correct answer quickly, please. :((
Urgent plz solve it within 30-40 mins I'll give you multiple upvote....hand written
Problem 1 (30 points): A 14 kg block falls through a channel which is lubricated by a thin layer of oil with thickness h and viscosity u on both sides. The contact area between the wall and block on each side is A. Determine the terminal velocity, V, of the block given A = 55 cm², µ = 0.35 kg ,and h = 2 mm. m'S %3D Oil film (thickness = || Block V
I need help on 4a
Hand written plzzz i'll give you multiple upvote....asap thanx
1. If a mercury barometer reads 700 mm and a Bourdon gauge at a point in a flow system reads 500 kN/m², what is the absolute pressure at the point? [Ans. 595 kN/m² abs.]
Problem-2 For the turbulent incompressible boundary layer, the velocity profile is given as u/Ue, y = y/8, Ue and d are boundary-layer edge velocity where, u = and boundary layer thickness, respectively. Using momentum integral equation, prove that: 8/x = 0.383/Re,/5 8% /x = 0.0479/Re/5 and 0/x = 0.0372/Re/5
Corection the following number k=.02625,Kinematic viscosity(fancy v)=16.55*10^-6m^2/s,Pr=.7 Re(x=L)=54380 Nu(x)=170.1 h(x=L)=29.8 Ts(l)=54.9C
I need help on 4b
Find P for impending motion ma = 150 kg, mb = 200 kg, Pi=0.1, µ2= 0.3 A 45 B P.