2. Air at 40 °C moves over a long flat plate with a uniform free stream velocity of U = 900 m/s. Assume the boundary layer formed above the surface of the plate starts at the tip of the leading edge and the velocity profile inside the boundary layer has power-law form as Re, <107 {8 10’ < Re, < 10* 9 10* < Re, <10° 7 ,for u Sx
Q: A vertical air stream flowing at a velocity of 100 m/s supports a ball of 60 mm in diameter. Taking…
A: Given data, V= 100 m/s, D=60 mm= 0.06 m ρ=1.2 kg/m³ v= 1.6 stokes Cd= 0.8
Q: A helicopter during a test has its four blades turning at 89 rpm with the blades oriented parallel…
A: Given data:- length of blade=3.5m ρair=1.225 kg/m3 width of blade=200mm…
Q: Estimate the annual production of a 12 m diameter horizontal axis wind turbine operating at standard…
A: given data- turbine diameter, d = 12 m air density r = 1.225 kg/m3 average wind velocity v = 8 m/s…
Q: The next figure shows a symmetric two dimensional wedge of half angle of 15°: If the wedge is well…
A: Given: Mach number = 3.5 T = 20 deg C
Q: Air at 15°C forms a boundary layer near a solid wall. The velocity distribution in the boundary…
A: Given, Temperature T = 15o C U = 35 m/s δ=0.8 cm
Q: 5- Air at 20C is flowing Over a flat plate at 3m/s. If the plate is 30 cm width and at 60 C…
A:
Q: On March 16, 1990, an Air Force SR-71 set a new continental speedrecord, averaging a velocity of…
A:
Q: Please don't provide handwritten solution.
A: The given parameters are:Freestream temperature, T∞ = 245 KFreestream pressure, p∞ = 4.35 × 10^4…
Q: Q9-A block 0.2 m square, with 5 kg mass, slides down a smooth incline, 30° below the horizontal, a…
A:
Q: A hydrofoil 51 cm long 4 m wide moves at 1m/s in water at temperature 20 C. Use laminar boundary…
A: Given Data⇒ Length of the hydrofoil is L=51 cm L=0.51 m w=4 m Velocity is v=1ms At T=200C Laminar…
Q: A model of the Airbus 320 is tested in a wind tunnel using air at standard conditions. If the tunnel…
A:
Q: A gas with density 1.3kg/m and dynamic viscosity 4air = 1.1 x 10-5Pa. s flows past a flat plate of…
A: Given:ρ=1.3 kg/m3μair=1.1*10-5 PaL=2.2 mB=1.2 mFs=1 N
Q: Air at 20°C forms a boundary layer near a solid wall, in which the velocity profile, U = Umax sin TY…
A:
Q: A fluid with viscosity of u = 1.752 x 10-5kg/m. s and density of p= 1.2kg/m³ %3D flows at U=1 m/s…
A: We have to determine (a) Find the boundary layer thickness at the end of the plate. (b) Find the…
Q: QI/ If the velocity profile of the boundary layer is =-O find the thickness of boundary Uo 28 layer,…
A: Momentum Thickness,θ=∫0δuu∞1-uu∞dy…
Q: A- Two large surfaces are 2.2 cm wide of infinite extent contains a fluid with an absolute viscosity…
A: Given data : width of infinite extension = 2.2 cm Absolute viscosity of the…
Q: KNOWN: Speed and temperature of atmospheric air flowing over a flat plate of prescribed length and…
A:
Q: distance of 1 m from the leading edge of a flat plate, kept at zero angle of incidence to the flow…
A: Given:x1=1 mx4=4 mδ1=0.1 cm
Q: 7,(1 – n), 5.10 In a laminar boundary layer, the shear stress distribution is given as t= T where n…
A:
Q: (c) If the velocity profile in a boundary layer was approximated by the quadratic distribution u =…
A: Given-Data:- Quadratic distribution equation,u = Ay2+By+C To-Determine:- uU = 2yδ-yδ2ζo =…
Q: Consider a flat plate at zero angle of attack in an airflow at standard sea level conditions (p∞ =…
A: Given data: Sea level conditions: P∞=1.01×105 N/m2, T∞=288K, μ∞=1.7894×10-5 kg/(m.s) Also for air…
Q: An air-hockey puck has a mass of 50 g and is 9 cm in diameter.When placed on the air table, a 20 °C…
A: Given a) Time required to slow down puck to 1m/s can be determined as
Q: The drag equation for the Gofaster 172 is: D = 0.0003v2A. D is drag in pounds; v is airspeed in…
A:
Q: An air current impinges laterally on an isolated train car of dimensions 3 m high, 12.2 m long and…
A:
Q: Sir Isaac Newton measured the speed of sound by timing the difference between seeing a cannon's puff…
A:
Q: What is the most important criterion for use of the modified pressure P′ rather than the…
A: Navier-Stokes equation is used for determining properties of incompressible Newtonian Fluids.
Q: Sir Isaac Newton measured the speed of sound by timing the difference between seeing a cannon's puff…
A: Given: The distance between the canon and the Newton = 5.4 ml The time is taken to travel = 24.94 s…
Q: A buoyant ball of specific gravity SG < 1 dropped intowater at inlet velocity V0 will penetrate a…
A: Now write the expression for the buoyant force.
Q: (b) The velocity profile in the laminar boundary layer can be approximated by the equation: 3 Us…
A:
Q: Sir Isaac Newton measured the speed of sound by timing the difference between seeing a cannon's puff…
A:
Q: Consider the boundary layer near the forward stagnation point of a 2D body, say a circular cylinder.…
A: given; Ux=axux=axf'(η)where;η=yg(x)y=η*g(x)
Q: Assuming air resistance with drag ratio =0.50 find the terminal velocity for an object, initially…
A:
Q: Consider a large dirigible (like the Goodyear blimp) with length L = 240 m, and average diameter D =…
A:
Q: 6- A uniform free stream of air at 0.8 m/s flows over a flat plate (4 m long x 1 m wide). Assuming…
A: The drag force on a flat plate can be determined as, For the laminar flow the drag coefficient can…
Q: What is the power per unit area of a 10 knot uniform wind (in W/m²)?
A:
Q: cool not coPP I in air at 25°C and latm. Use drag coefficient C the spheres fall at their terminal…
A: Re =ρVDμ =VDν chracterstics of air at Ts+T∞2=300+3502= 325 K using data book ν =5.12×10-5m2/s k =…
Q: 2. You are working for a glider manufacturer and have been asked to analyse the laminar boundary…
A: For the solution refer below images.
Q: Which of the following boundary conditions is NOT valid for laminar boundary layer flow over a flat…
A: Since all are different questions and as per the guideline, I an solve one question at a time. For…
Q: For both fluids, and at several x locations: a. Plot The resultant velocity profiles within the…
A:
Q: Question 2 Air flow at a constant speed (Us = 10 m/s) is forming a two-dimensional incompressible…
A:
Q: Given Information: dy dv Cd The system of equations = v, = -g– mv |v| , for the position and…
A: The drag force problem, Area of the ball needs to be calculated.
Q: Consider parallel flow over a flat plate for air at 300 K and engine oil at 380 K. The free stream…
A: To Find : a) The location where transition to turbulence occurs, for both fluids.(b) The velocity…
Q: (b) A Formula 1 team tests their car in a wind tunnel at a scale of 50%, at a speed of VwinaTunnet =…
A: Given data: - The testing speed at wind tunnel on model car is vm = 50 m/s. The measured downward…
Q: The test section of a low speed wind tunnel is a square duct with cross section of 7 cm × 7 cm. The…
A: In fluid mechanics, continuity equation represents the flow rate of the fluid flowing through a…
Q: A thin flat plate is positioned in a wind tunnel parallel to the wind direction (Figure below). Air…
A:
Q: Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞= 4.35…
A: The constant value of entropy is maintained anytime there is a reversible and adiabatic flow,…
Step by step
Solved in 3 steps with 3 images
- Consider liquid in a cylindrical tank. Both the tank and the liquid rotate as a rigid body. The free surface of the liquid is exposed to room air. Surface tension effects are negligible. Present the boundary conditions required to solve this problem. Specifically, what are the velocity boundary conditions in terms of cylindrical coordinates (r, 0, z) and velocity components (ur, uo, U:) at all surfaces, including the tank walls and the free surface? What pressure boundary conditions are appropriate for this flow field? Explain. Free surface Ps Paa LiquidNeed Solution through 15minPu Wings at supersonic flows can be modeled as a flat plate that have constant pressure distributions across their chord. Ignoring any viscous effects determine the drag force of the wing section. Round to the full N/m and make sure you use the standard sign convention (i.e. right hand rule). Use the following data chord = 1.5 m epsilon = 5 degree angle of attack = 20.0 alpha upper surface pressure = 60,000 Pa lower surface pressure = 150,000 Pa
- a. If the velocity distribution for the laminar boundary layer over a flat plate is given by :- ** (²) ² - 21 + A₂ x U A₁ + A₂ x Determine the form of the velocity profile by using the necessary boundary conditions. After that by using the Von-Karman integral momentum equation find an expression in terms of the Reynolds number to evaluate 1- Boundary Layer Thickness Force 2-Wall Shear Stress 3-Drag 5- Displacement Thickness + A₁ x 4- Local and Average Skin Friction Coefficients 6- Momentum Thickness 7- Energy ThicknessQuestion 2 a) A laminar boundary layer profile may be assumed to be approximately of the form u/Ue = f (n)=f(y/8) i) Use an integral analysis with the following two-segment velocity profile, ƒ (n)=(n/6)(10–3n−n³), for 0≤n≤0.293 and ƒ (n) = sin(лn/2) for 0.293≤ŋ≤1, to find expressions for the displacement thickness &*, the momentum thickness 0, the shape factor H, the skin-friction coefficient of, and the drag coefficient CD. ii) Derive an expression for the velocity normal to the stream wise direction given that, u/U₂ = f(n). iii) Hence obtain the velocity normal to the stream wise direction for the above two- segment velocity profile.(b) A smooth thin plate 10 m long and 1 m wide is placed in an air stream at 3 m/s with its length parallel with the flow. Determine the total drag force acting on the plate if the air temperature is 30°C. (c) Based on question Q4(b), determine the total drag force acting on the thin plate if the length of the plate is 3 m long and the air stream velocity is 1 m/s.
- 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 isConsider the boundary layer flow = 1 - (1 − 2)¹5, 0Consider the boundary layer flow=1-(1-)1.5, 0Air 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.A ship 200 f t long with a wetted area of 5000 ft2 moves at 25 ft/s. Find the friction drag, assuming that the ship surface may be modeled as a flat plate, and ρ = 1.94 slugs/ft3 and ν = 1.2 × 10−5 ft2/s. What is the minimum power required to move the ship at this speed?A jet of ethylene exists a 40 mm diameter nozzle into still air at 300K and 1 atm. Compare the spreading angles and axial locations where the jet centreline mass fraction drops to the stoichiometric value for initial jet velocities of 20 cm/s and 2 cm/s. The viscosity of ethylene at 300K is 102.3*10^-7 N.s/m^2SEE MORE QUESTIONSRecommended textbooks for youElements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill EducationControl Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEYElements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill EducationControl Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY