From the laminar boundary layer the velocity distributions given below, find the momentum thickness θ, boundary layer thickness δ, wall shear stress τw, skin friction coefficient Cf , and displacement thickness δ*1. A linear profile, u(x, y) = a + by 2. von K ́arm ́an’s second-order, parabolic profile,u(x, y) = a + by + cy23. A third-order, cubic function,u(x, y) = a + by + cy2+ dy34. Pohlhausen’s fourth-order, quartic profile,u(x, y) = a + by + cy2+ dy3+ ey45. A sinusoidal profile,u = U sin (π/2*y/δ)

“Since you have asked multiple question, we will solve the first question for you. If you want any…

From the laminar boundary layer the velocity distributions given below, find the momentum thickness θ, boundary layer thickness δ, wall shear stress τw, skin friction coefficient Cf , and displacement thickness δ* 1. A linear profile, u(x, y) = a + by

From the laminar boundary layer the velocity distributions given below, find the momentum thickness θ, boundary layer thickness δ, wall shear stress τw, skin friction coefficient Cf , and displacement thickness δ* 1. A linear profile, u(x, y) = a + by

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

See similar textbooks

Related questions

Q: A sphere 6.0 cm in diameter, D, is fixed in airflow (see Figure). The approach velocity, V, is 4.0…

A: 1. Reynolds number Re =vDν 2. CD vs Reynolds number chart is used to get the value of drag…

Q: Vortices are usually shed from the rear of a cylinder, which are placed in a uniform flow at low…

A: Given variables are –

Q: A prototype submarine moves at velocity V, in fresh water at 20 °C, at a 2-m depth, where ambient…

A: Given Depth, h = 2 m Pressure, P = 128 kPa Cavitation number, Ca = 0.25 Find Velocity, v

Q: Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m. Calculate…

A: Given: The velocity of the air, V = 10 m/s length of the plate, L = 1.52 m The width of the plate, W…

Q: The momentum thickness OM for laminar flow over a flat plate is (115/1134) 6. Find the following: a)…

Q: Consider the following examples: • 55 mph NE • 173 lb horizontal • 9.8067 m/s? down The above…

A: Scalar Quantities:-Scalar Quantities are those physical quantities who have only magnitude but no…

Q: Consider two pressure taps along the wall of a laminar boundary layer as in Fig. The fluid is air at…

A: Write the assumption of the flow. The flow is steady, incompressible, and laminar. The boundary…

Q: Example 1.10 gave an analysis that predicted that theviscous moment on a rotating disk M = πμ V R 4…

A: The expression of the viscous moment for a rotating disk, The uncertainty of each variable is given…

Q: 1. A two dimensional supersonic airfoil has the cross-section shown below (base: 2.8 m, base angles…

A: Given Mach number, M = 2.4 Pressure, P = 25 kPa Base, w = 2.8 m…

Q: Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23…

A: Given: The density of fluid at sea level, ρ = 1.23 kg/m3 = 0.002377 slug/ft3 The pressure at sea…

Q: A laminar boundary layer is observed to grow on a flat plate such that the pressure is constant…

A: Write the expression for displacement thickness.

Q: We are testing a flat plate of length L = 1.125 m and width W = 0.225 m in a stream of air flowing…

A: For flat plate boundary layer conditionWe Re=5×105Thus Re=ρVLμ Re=1.2×20×1.12518×10-6 Re=15×105Thus…

Q: A seA A, soA A solid cylinder of diameter d, length and density p, falls due to gravity inside a…

Q: Liquid flows tangentially past a flat plate. The fluid properties are u=10° N.S/m² and p=1.5 kg/m³.…

Q: Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m. Calculate…

A: Boundary layer thickness is the distance from the plate in a vertical direction up to where velocity…

Q: If the laminar velocity profile is approximated by the cubic-order polynomial where, a = u/U, and y…

A: a) The given velocity profile is uUe =a1+a2yδ+a3yδ2+a4yδ3 (1) The boundary…

Q: A solid cone of angle 24, tase 1,, and denisity p, is rotat- Ing with initial angulár velocity my…

A: Given: 1. TO determine: Relation for angular velocity

Q: 7.4 Consider a disk of radius R rotating in an incompressible fluid at a speed w. The equations that…

Q: Air at 20°C flows at V = 8.5 m/s parallel to a flat plate Fig.. The front of the plate is well…

A: Given that, Temperature of air, T=20 °C,Velocity of air, V=8.5 m/s,Length of plate, L=40…

Q: QUESTION 5 A circular tank of diameter 80 cm contains water up to a height of 12 000 mm. The tank is…

A: Free vortex flows are plane circular vortex flows in which the total mechanical energy in the entire…

Q: An air hockey puck has a mass of 50 g and is 9 cm in diameter. When placed on the air table, a 40…

A: (a) On using Sutherlands Law, The viscosity of air at 40 oC is written as

Q: An aluminum cylinder weighing 30 N, 6 cm in diameterand 40 cm long, is falling concentrically…

A: Given: The weight of the cylinder is w= 30 N. The diameter and length are D= 6 cm=0.06m and L=40…

Q: Let the vortex/sink flow of Eq. (8.16) simulate a tornado as inFig. . Suppose that the circulation…

A: Given data: The circulation about the tornado is; Γ=8500 m2s. The pressure at the radial distance…

Q: "A maximum 10-minute mean wind of 124 km/h was registered at North Point anemometer located inside…

Q: A NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level…

Q: The large block shown is x = 72 cm wide, y = 54 cm long, and z = 9.0 cm high. This block is passing…

A: Given:x=72 cm or 0.72 my=54 cm or 0.54 mz=9 cm or 0.09 mρ=1.43 kg/m3v=8.61 m/s

Q: Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m. Calculate…

A: Air temperature, T=20oC Air speed, V=10 m/s Length of the flat plate, L=1.52 m Width of the plate,…

Q: SAE 30 oil at 20 °C flows at 1.8 ft3/s from a reservoir into a6-in-diameter pipe. Use flat-plate…

A: The velocity of the oil,

Q: Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23…

A: Given: An inviscid and incompressible flow ρ=1.23 kg/m3P=1.01×105N/m2 To find: if velocity V∞ is…

Q: Air flows parallel to a speed limit sign along the highway at speed V = 8.5 m/s. The temperature of…

A: Given data: The speed of air, V = 8.5 m/s. The length of highway, L = 0.45 m. Refer the table…

Q: Q3) In some wind tunnels the test section is perforated to suck out fluid and provide a thin viscous…

A: Given Data : Number of holes = 12064 diameter of hole = 5 mm suction velocity Vs = 8 m/s Entrance…

Q: Reference 12 contains inviscid theory calculations for the upper and lower surface velocity…

A: For the same datum, the relation between the velocity and pressure between two points can be…

Q: An aluminum cylinder weighing 30 N, 6 cm in diameter and 40 cm long, is falling concentrically…

A: Given that, Calculate the clearance between the diameter of sleeve and aluminum cylinder

Q: (a) Use the y-momentum equation to show that the pressure gradient across the boundary layer is…

Q: In the Blasius equation stream function: j is a dímensionless plane p(x, y) f(n) VDUX Values of f…

A: Given,fη=ψx,yvUx (Blasius equation)η=2f(2.0)=0.6500U∞=6 m/secAt P=1 atm T=20 °CKinematic visocity,…

Q: A cylinder 4 ft in diameter is placed in an air stream where the free-stream velocity is 100 ft/s.…

A: Given: r= 4 ftU∞=100 ft/sθ1=45°θ2=135°

Q: During the 1920s and early 1930s, the NACA obtained wind tunnel data on different airfoils by…

A: Given Data: The aspect ratio is AR=6. The wing area is Aw=1.5 ft2. The velocity is V=100 ft/sec.…

Q: A solid cylinder of diameter D, length L, and density p, falls due to gravity inside a tube of…

A: The weight of the cylinder can be expressed as,

Q: An airfoil is in a freestream where p.(assigned altitude)atm, p(density) (assigned altitude) kg/m3,…

A: GivenP∞=36.22atmP=0.5atmV∞=980m/s ρ=36.22kg/m3

Q: A hovercraft weighs M = 1500 kg and hovels without changing altitude. The exit flow exhausts to…

A: The volume flow rate and mass flow can be given as –

Q: Consider two different flows over geometrically similar airfoil shapes,one airfoil being twice the…

A: Write the expression for Mach number. Here, V represents the velocity of flow over the airfoil and…

Q: Consider steady flow of air through the diffuser portion of a wind tunnel. Along the centerline of…

A: Given: centerline air speed decreases parabolically through the diffuser To write An for…

Q: Question 11) Vortices are usually shed from the rear of a cylinder, which are placed in a uniform…

A: (1) The given variables are: Frequency: f The velocity of the stream: V Fluid density: ρ Fluid…

Q: Algebraic equations such as Bernoulli's relation, Eq. (1) of Ex. 1.3, are dimensionally consistent,…

A: The x-momentum boundary layer equation derived by Ludwig Prandtl is given as,…

Q: A smooth, flat plate, 3.0 meters wide and 0.6 meters long parallel to the flow, is immersed in 15°C…

Q: 6.22 This planar water jet (60°F) is deflected by a fixed vane. What are the x- and y-components of…

Question

2. von K ́arm ́an’s second-order, parabolic profile,u(x, y) = a + by + cy2

3. A third-order, cubic function,u(x, y) = a + by + cy2+ dy3

4. Pohlhausen’s fourth-order, quartic profile,u(x, y) = a + by + cy2+ dy3+ ey4

5. A sinusoidal profile,u = U sin (π/2*y/δ)

Expert Solution

This question has been solved!

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

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1

VIEW

Step 2

VIEW

Trending now

This is a popular solution!

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

Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. The lift on a spinning circular cylinder in a freestream with a velocity of30 m/s and at standard sea level conditions is 6 N/m of span. Calculate thecirculation around the cylinder.
Air flows parallel to a speed limit sign along the highway at speed V = 8.5 m/s. The temperature of the air is 25°C, and the width W of the sign parallel to the flow direction (i.e., its length) is 0.45 m. Is the boundary layer on the sign laminar or turbulent or transitional?
A solid cone of angle 2Ɵ, base r 0 , and density ρ c is rotating with initialangular velocity ω 0 inside a conical seat,as shown below. The clearance h is filled with oilof viscosity μ. Neglecting air drag, derive an analytical expression for thecone’s angular velocity ω(t) if there is noapplied torque.
Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. Consider the lifting flow over a circular cylinder of a given radius and witha given circulation. If V∞ is doubled, keeping the circulation the same,does the shape of the streamlines change? Explain.
Consider a rectangular wing mounted in a wind tunnel. The wing model completely spans the testsection so that the flow sees essentially an infinite wing. The wing has a NACA 2421 airfoil section,a chord of 3.0 m, and a span of 20 m. The tunnel is operated at the following test conditions: P =101,000 N/m2; T = 35° C; V = 50 m/s; and µ = 1.9 * 10 -5 kg/(m s).(a) Determine the operating Reynolds number.(b) Calculate the lift, drag, and moment about the aerodynamic center for an angle of attack of 8 deg andRe=9*106(c) At a Reynolds number of 3 * 106, find the following:1) What is the stalling angle of attack for this airfoil?2) What is the angle of attack for zero lift?3) What is the lift-curve slope?
Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. Derive the velocity potential for a doublet.
Please indicate the given, assumption and illustration. A source with strength 0.25 m2/s and a vortex with strength 1 m2/s (counter-clockwise) are located at the origin. After working out the equations for the stream function and velocity potential components, determine the following velocity components at a point P(1, 0.5): A) The Radial Velocity component in meters/second. B) The Tangential Velocity Component in meters/second.
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m. Calculate the boundary layer thickness at the trailing edge of plate and drag force on one side of plate if: a. Surface of plate is smooth.b. Surface of plate is rough. The air properties at 20 °C are: Density, ? = 1.2 kg/m3 and dynamic viscosity, ? = 1.8 x 10^-5 kg/m·s and kinematic viscosity, ν = 1.516×10^-5 m2/s.
SAE 30 oil at 20 °C flows at 1.8 ft3/s from a reservoir into a6-in-diameter pipe. Use flat-plate theory to estimate theposition x where the pipe wall boundary layers meet in thecenter. Compare with Eq., Le/d≈ 0.06 Red laminar and give some explanationsfor the discrepancy.
During the 1920s and early 1930s, the NACA obtained wind tunnel data on different airfoils by testing finite wings with an aspect ratio of 6. These data were then “corrected” to obtain infinite-wing airfoil characteristics. Consider such a finite wing with an area and aspect ratio of 1.5 ft 2 and 6, respectively, mounted in a wind tunnel where the test-section flow velocity is 100 ft/s at standard sea-level conditions. When the wing is pitched to α = −2°, no lift is measured. When the wing is pitched to α = 10°, a lift of 17.9 lb is measured. Calculate the lift slope for the airfoil (the infinite wing) if the span effectiveness factor is 0.95
Vortices are usually shed from the rear of a cylinder, which are placed in a uniform flow at low speeds. The vortices alternatively leave the top and the bottom of the cylinder, as shown in figure, causing an alternating force normal because of generating a dimensionless relationship for Kármán vortex shedding frequency fk (1/s) as a function of free-stream speed V(m/s), fluid density r (kg/m3), fluid viscosity µ (kg/m.s), sound velocity c (m/s), surface roughness ɛ (m) and cylinder diameter D(m). Solve the problem by making the necessary assumptions and drawing the schematic figure. I-Determine the nondimensional p parameters using repeating variables, involving f, ɛ, c and µ as nonrepeating variables ii-the dynamics of Bhosphorus bridge is investigated in a wind tunnel for the vortex generation behind the wires. A 1/56,2 scaled down model of the hanging wires is used in the laboratory. If vortex shedding frequency of of Bhosphorus bridge 562 Hz is measured in the laboratory at…
A smooth wooden sphere (SG = 0.65) is connected by athin rigid rod to a hinge in a wind tunnel, as in Fig. Air at 20°C and 1 atm flows and levitates the sphere.(a) Plot the angle θ versus sphere diameter d in the range1 cm≤ d≤15 cm. (b) Comment on the feasibility of thisconfiguration. Neglect rod drag.