Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 19, Problem 19.2P
For the case in Problem 19.1, calculate the boundary-layer thickness at the trailing edge for
a. Completely laminar flow
b. Completely turbulent flow
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Chapter 19 Solutions
Fundamentals of Aerodynamics
Ch. 19 - The wing on a Piper Cherokee general aviation...Ch. 19 - For the case in Problem 19.1, calculate the...Ch. 19 - For the case in Problem 19.1, calculate the...Ch. 19 - Consider Mach 4 flow at standard sea level...Ch. 19 - Repeat Problem 19.4 for the case of all turbulent...Ch. 19 - Prob. 19.6PCh. 19 - Prob. 19.7P
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- A bulk liquid transport truck incorporates a cylindrical tank 3m in diameter and 10m long. For the tank alone, calculate the pressure drag when the truck is traveling at 80km/h in air at 0°Carrow_forwardEngine oil at 100C flows over and parallel to a flat surface at a velocity of 3 m/s. Calculate the thickness of the hydrodynamic boundary layer at a distance 0.3 m from the leading edge of the surface.arrow_forwardExplain the following: Flow separation over an airfoil occurs at high angle of attack. Lift coefficient of a wing is less than lift coefficient of the airfoil that makes up that wing. High lift devices are needed during takeoff and landing.arrow_forward
- Derive an expression for turbulent boundary layer thickness over a flat platearrow_forwardFlow straighteners are arrays of narrow ducts placed inwind tunnels to remove swirl and other in-plane secondaryvelocities. They can be idealized as square boxes constructedby vertical and horizontal plates, as in Fig. .The cross-section is a by a, and the box length is L. Assuminglaminar flat-plate flow and an array of N x N boxes,derive a formula for (a) the total drag on the bundle ofboxes and (b) the effective pressure drop across the bundle.arrow_forwardAn antenna in the shape of a cylindrical rod projects from the top of a locomotive. If the antenna is 42 in long and 0.200 in. in diameter, compute the drag force on it when the locomotive is traveling at 160 mph in still air at -20°F.arrow_forward
- Water at 60° C flows over 2.5 cm square flat plate 90°C at a velocity of 4 m/s. 1- Calculate the drag force , Xcritical 2- If the flat plate is exposed to the natural air convection at 60 °C instead of water with same values of temperatures and length calculate Rayleigh number.arrow_forwardConsider the NACA 2412 airfoil, data for which is given in 4.10 and 4.11. The data are given for two values of the Reynolds number based on chord length. For the case where Rec = 3.1×106, estimate: (a) the laminar boundary layer thickness at the trailing edge for a chord length of 1.5 m and (b) the net laminar skin-friction drag coefficient for the airfoil.arrow_forward2.A fluid at a temperature of 75 oC flows at a speed of 10 m/s across a pipeouter diameter of 5 cm.Calculate the drag coefficient and drag force per meter length if the fluid flowing is:a) Air at a pressure of 1 atmb) CO2 gas at a pressure of 1 atm liquidd) Ethylene glycole) Engine oilf) What is your discussion and conclusion?arrow_forward
- What is the Effect of wing plan form (taper ratio and wing twist) and aspect ratio(AR) on the Induced drag coefficient, ?arrow_forwardFairings are attached to the front and back of a cylindrical body to make it look more streamlined. What is the effect of this modification on the (a) friction drag, (b) pressure drag, and (c) total drag? Assume the Reynolds number is high enough so that the flow is turbulent for both cases.arrow_forwardConsider a circular cylinder in a hypersonic flow, with its axisperpendicular to the flow. Let φ be the angle measured between radiidrawn to the leading edge (the stagnation point) and to any arbitrary pointon the cylinder. The pressure coefficient distribution along the cylindricalsurface is given by Cp = 2 cos2 φ for 0 ≤ φ ≤ π/2 and 3π/2 ≤ φ ≤ 2πand Cp = 0 for π/2 ≤ φ ≤ 3π/2. Calculate the drag coefficient for thecylinder, based on projected frontal area of the cylinder.arrow_forward
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