Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN: 9781305387102
Author: Kreith, Frank; Manglik, Raj M.
Publisher: Cengage Learning
expand_more
expand_more
format_list_bulleted
Concept explainers
Question
error_outline
This textbook solution is under construction.
Students have asked these similar questions
Air at 20°C flows at V = 80.0 m/s over a smooth flat plate of length L = 17.5 m. Plot the turbulent boundary layer profile in physical variables (u as a function of y) at x = L. Compare the profile generated by the one-seventh-power law, the log law, and Spalding’s law of the wall, assuming that the boundary layer is fully turbulent from the beginning of the plate.
What are the physical and quantitative evidence of turbulence in fluid flow?
Air at 20°C and 1 atm flow at 20 m/s past the flat platein Fig. . A pitot stagnation tube, placed 2 mm fromthe wall, develops a manometer head h = 16 mm of Meriamred oil, SG = 0.827. Use this information to estimatethe downstream position x of the pitot tube. Assumelaminar flow.
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
- Water flows at a velocity of 1.2 m/s over a flat plate 1.2 m long. Assume 1/7thpower law and determine the boundary layer thickness and displacementthickness. Compare the values with values calculated using laminar flowcorrelations. υ = 1 × 10−6m2/s.arrow_forwardThe standard sea level value of viscosity coefficient for air is μ = 1.7894×10−5 kg/(m · s) = 3.7373 × 10−7 slug/(ft · s). The wing on a Piper Cherokee general aviation aircraft is rectangular, witha span of 9.75 m and a chord of 1.6 m. The aircraft is flying at cruisingspeed (141 mi/h) at sea level. Assume that the skin-friction drag on thewing can be approximated by the drag on a flat plate of the samedimensions. Calculate the skin-friction drag:a. If the flow were completely laminar (which is not the case in real life)b. If the flow were completely turbulent (which is more realistic)Compare the two results.arrow_forwardFor the velocity components (in cylindrical coordinates) u=-10(1-1/r2)cosθ, v=10(1+1/r2)sinθ, w=0 determine the expression of pressure for incompressible frictionless fluid flow in the absence of body force. Also check whether the equation of motion is satisfied or not.arrow_forward
- Consider a commercial airliner flying at a speed of 540 mph (relative to the air) at analtitude of 30,000 feet. (c) With a mean molar mass of M = 28.9 g/mol, determine the Reynolds number andMach number in flight. Justify your choice of characteristic length by referencinga commercial aircraft currently in service.(d) Is this flow inviscid or viscous? Is this flow subsonic or supersonic? Qualitativelydescribe the differences between these flight regimes.arrow_forwardConsider two pressure taps along the wall of a laminar boundary layer as in Fig. The fluid is air at 25°C, U1 = 13.7 m/s, and the static pressure P1 is 2.96 Pa greater than static pressure P2, as measured by a very sensitive differential pressure transducer. Is outer flow velocity U2 greater than, equal to, or less than outer flow velocity U1? Explain. Estimate U2arrow_forwardOutside an inner, intense-activity circle of radius R , a tropicalstorm can be simulated by a polar-coordinate velocitypotential ϕ ( r , θ ) = U o R θ , where U o is the wind velocity atradius R . ( a ) Determine the velocity components outsider = R . ( b ) If, at R = 25 mi, the velocity is 100 mi/h and thepressure 99 kPa, calculate the velocity and pressure atr =100 mi.arrow_forward
- IBL, Flat Plate. Apply the integral boundary layer analysis to a flat plate turbulent flow as follows. Assume the turbulent profile u/U = (y/δ)1/6 to compute the momentum flux term on the RHS of IBL, but on the LHS of IBL, use the empirical wall shear stress, adapted from pipe flow: ?w = 0.0233 ⍴U2 (v/Uδ)1/4 where the kinematic viscosity ν = μ/⍴. It is necessary to use this empirical wall shear relation because the turbulent power law velocity profile blows up at the wall and cannot be used to evaluate the wall shear stress. Compute (a) (δ/x) as a function of Rex; (b) total drag coefficient, CD, L as a function of ReL; (c) If ReL = 6 x 107 compare values for this IBL CD,L and those empirical ones given in Table 9.1 for both smooth plate and transitional at Rex = 5 x 105 cases. Note: You must show all the algebra in evaluating the IBL to get full credit. Ans OM: (a) (δ/x) ~ 10-1/(Rex)1/5; (b) CD,L ~ 10-2/(ReL)1/5; (c) CD,IBL ~ 10-3; CD,Smooth ~ 10-3; CD,Trans ~ 10-3arrow_forwardA vertical air stream flowing at a velocity of 100 m/s supports a ball of 60 mm in diameter. Taking the density of air as 1.2 kg/m³ and kinematic viscosity as 1.6 stokes, the weight of the ball that is supported is (if coefficient of drag C= 0.8)arrow_forwardAir 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 sideof 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/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. kindly give me the solution of this problem with correct and logical reasoning.arrow_forward
- 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 sideof 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/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. I got the first solution which was wrong kindly solve it correctlyarrow_forwardAssume 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.arrow_forwardA stirrer mixes liquid chemicals in a large tank. The free surface of the liquid is exposed to room air. Surface tension effects are negligible. Discuss the boundary conditions required to solve this problem. Specifically, what are the velocity boundary conditions in terms of cylindrical coordinates (r, ?, z) and velocity components (ur, u?, uz) at all surfaces, including the blades and the free surface? What pressure boundary conditions are appropriate for this flow field? Write mathematical equations for each boundary condition and discuss.arrow_forward
arrow_back_ios
SEE MORE QUESTIONS
arrow_forward_ios
Recommended textbooks for you
- Principles of Heat Transfer (Activate Learning wi...Mechanical EngineeringISBN:9781305387102Author:Kreith, Frank; Manglik, Raj M.Publisher:Cengage Learning
Principles of Heat Transfer (Activate Learning wi...
Mechanical Engineering
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Cengage Learning
8.01x - Lect 27 - Fluid Mechanics, Hydrostatics, Pascal's Principle, Atmosph. Pressure; Author: Lectures by Walter Lewin. They will make you ♥ Physics.;https://www.youtube.com/watch?v=O_HQklhIlwQ;License: Standard YouTube License, CC-BY
Dynamics of Fluid Flow - Introduction; Author: Tutorials Point (India) Ltd.;https://www.youtube.com/watch?v=djx9jlkYAt4;License: Standard Youtube License