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
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- Air flows over a flat plate with a velocity u = 13 m/s and temperature T. = 25 °C. The plate surface area and temperature are A = 2 x 2 m and T, =125 °C, respectively. a- Determine the critical length X (length of the laminar region). b- Determine the rate of heat transfer in the laminar region. %3D C- Determine the total rate of heat transfer from the entire plate (mixed boundary layer). Use the following properties of air H = 2.08 x 10 N.s/m, p = 0.887 kg/m, k = 0.0325 W/m.K, Pr = 0.705 %3D rinar @111Help me pleaseHandwritten plzz asap thank you plzzzzz urgent plzzz solve plzzzzzz...asap i'll give you upvote sure...
- A cylinder 4 ft in diameter is placed in an air stream where the free-stream velocity is 100 ft/s. 1/ What is the vortex strength required to place the stagnation points at 0= 45° and 0 = 135? Does the vortex rotate clockwise or counterclockwise? 2/ Given the freestream pressure of 1967 Ibf/ft? and freestream temperature of 68F, calculate the pressure at the stagnation points? Hint: first find the freestream density.Need 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
- PART A -5 For Air Assume: v=1.46×10 m²/s and p =1.225 kg/m³ Question A1 A flat plate with unit width is placed in a uniform steady two-dimensional flow of air with negligible pressure gradient. The velocity distribution of the boundary layer forming on either side of this plate has been given as: U /Us = 2.0(y/ 8) - (y/8)2.0, where U = 10 m/s. 1- Find and expression for the boundary layer thickness as a function of Rex. 2- At x=1.0 m calculate the shear stress corresponding to the points y=0.0,3.0 and 10.0 mm. 3- Calculate the boundary layer displacement and momentum thicknesses at x=1.0m. By using the calculated momentum thickness determine the drag force acting on one side of the plate between its leading edge and x = 1.0m. 4- At x=1.0m, calculate the mass flow rate through the boundary layer (mkg/s per unit width of the plate). What is the corresponding mass flow rate if the flow was inviscid (m; kg/s per unit width of the plate)? 5- By using appropriate equation (s) explain how the…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.
- Consider the boundary layer flow = 1 - (1 − 2)¹5, 0Consider the boundary layer flow=1-(1-)1.5, 0A 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?SEE 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