Question 13) A boundary layer is a thin region (usually along a wall)in which viscous forces are significant and within which the flow is rotational. Consider a boundary layer growing along a thin flat plate. The flow is steady. The boundary layer thickness d (m) at any downstream distance x is a function of x (m), free-stream velocity V(m/s)', fluid properties fluid density p (kg m³), fluid viscosity µ (kgm.s), sound velocity c (m/s) and surface roughness & (m). i-Use the method of repeating variables to generate a dimensionless relationship between boundary layer thickness & (m) and other parameters. Show all your work in detail. ii-calculate the boundary layer thickness 8 (m) value for x=19 m, free-stream velocity V=180 (m/s)", fluid properties fluid density p=1.190 (kg/m³), fluid viscosity µ=1.890 x10$ (kg/m.s), sound velocity c=345 (m/s) and surface roughness e=0.015m (m). What should the velocity of wind tunnel test the similar in wind tunnel at the same temperature and pressure for 1/10 scale flat plate model to provide same Re and Ma. what do you think about your finding, explain, comment?

Question 13) A boundary layer is a thin region (usually along a wall)in which viscous forces are significant and within which the flow is rotational. Consider a boundary layer growing along a thin flat plate. The flow is steady. The boundary layer thickness d (m) at any downstream distance x is a function of x (m), free-stream velocity V(m/s)', fluid properties fluid density p (kg m³), fluid viscosity µ (kgm.s), sound velocity c (m/s) and surface roughness & (m). i-Use the method of repeating variables to generate a dimensionless relationship between boundary layer thickness & (m) and other parameters. Show all your work in detail. ii-calculate the boundary layer thickness 8 (m) value for x=19 m, free-stream velocity V=180 (m/s)", fluid properties fluid density p=1.190 (kg/m³), fluid viscosity µ=1.890 x10$ (kg/m.s), sound velocity c=345 (m/s) and surface roughness e=0.015m (m). What should the velocity of wind tunnel test the similar in wind tunnel at the same temperature and pressure for 1/10 scale flat plate model to provide same Re and Ma. what do you think about your finding, explain, comment?

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

Similar questions

Q.3 Air (density 1.2 kg/m3 and kinematic viscosity 15 centistokes) flows over a flat plate, at zero angle of incidence, at a velocity of 20 m/s. If Reynolds number at transition is taken as 2.5 × 105, maximum distance, from leading edge up to which the boundary layer remains laminar is
I need the answer as soon as possible
Q4) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force and coefficiet of drag in terms of Re for the velocity profile of laminar boundary layer u/U=4(y/8)-6(y/8)5. Calcate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 1m long and 0.5m wide at a velocity 0.9m/s, the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
2. Consider the boundary-layer momentum equation for steady incompressible flow in two dimen- sions: ди dpe ду du du + po ay dx Assume the viscosity, u, to be constant. What does this equation simplifies to at a stationary solid surface? Based on this result, is a boundary layer more likely to separate in a favourable gradient (pressure decreasing) or an adverse pressure gradient? Sketch the velocity profile of a boundary layer that is attached and one that is separated. pressure
Air at 20⁰c and 1 ATM flows over a flat plate, v= 35 m/s. The plate is 75 cm long and guarded at 60⁰c. Suppose the depth of one Units on Z, count the transfer of Calor from that plate.
Question 11) 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 altemating force normal because of generating a dimensionless relationship for Kánmán vortex shedding frequency f (1/s) as a function of free-stream speed V(7m/s), fluid density p (kgm³), fluid viscosity µ (kg/m.s), sound velocity c (m/s), surface roughness & (m) and cylinder diameter D(m). || I-Determine the nondimensional a parameters using repeating variables, involving f, , c and u as nonrepeating variables ii-the dynamics of Bhosphorus bridge is investigated in a wind tunnel for the vortex generation behind the wires. A 1/59 scaled down model of the hanging wires is used in the laboratory. If vortex shedding frequency of of Bhosphorus bridge 590 Hz is measured in the laboratory at 29 m/s. Then detemine the expected frequency in the actual case exposed to 190 km/h…
Information Momentum Balance
2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Yu 0 0.0952 0.0922 0.0588 0 Fx = dYu dx 5 Y₁ 0 -0.0254 -0.0144 -0.0052 0 PL Pd) d: dx Y = Yu (x) Calculate the drag and lift force on the airfoil by numerically evaluating the integrals = S₁² ( P₂₁ = ['(P₁ - F (P₁ - Pu)dx 0 y = Y₂ (x) Pu 1.000 -1.640 -0.786 -0.212 0 Fy x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.
The slip correction coefficient (C) for a particle with diameter 100 nm is: (assume: mean free path of air 2 = 0.066 um) (a) 1.0018 G2.8703 7. (b) 5.0174 (d) 1.0035 The terminal velocity (in cm/s) for a particle with diameter 10 um and Reynolds number Re 2.5x10: a6.7x10 (c) 1.7x103 8. (b) 3.3x10 (d) 3.3x105
The thrust F of a Free propeller, either aircraft of marine, depends upon density ρ, the rotation rate n in r/s, the diameter D, and the forward velocity V. Viscous effects are slight and neglected here. Tests of a 25-cm-diameter model aircraft propeller, in a sea-level wind tunnel, yield the following thrust data at a velocity of 20 m/s : Rotation Rate, r/min____4800____6000____8000 Measured thrust, N____6.1____19____47 Use the dimensionless data to predict the thrust, in Newtons, of a similar 1.6-m-diameter prototype propeller when rotating at 3800 r/min and flying at 225 mi/h at 4000-m standard altitude.
Fluid Mechanics Expert Please
6.6 The boundary layer thickness d at any section for a flow past a flat plate de- pends upon the distance x measured along the plate from the leading edge to the section, free stream velocity U and the kinematic viscosity v of the fluid. Show with the help of Rayleigh's indicial method of dimensional analysis that c (Ux/v) or %3D