Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.5P
Consider the flow over a
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Chapter 9 Solutions
Fundamentals of Aerodynamics
Ch. 9 - A slender missile is flying at Mach 1.5 at low...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Equation (8.80) does not hold for an oblique shock...Ch. 9 - Consider an oblique shock wave with a wave angle...Ch. 9 - Consider the flow over a 22.2 half-angle wedge. If...Ch. 9 - Consider a flat plate at an angle of attack a to a...Ch. 9 - A 30.2 half-angle wedge is inserted into a...Ch. 9 - Consider a Mach 4 airflow at a pressure of 1 atm....Ch. 9 - Consider an oblique shock generated at a...Ch. 9 - Consider the supersonic flow over an expansion...
Ch. 9 - A supersonic flow at M1=1.58 and p1=1atm expands...Ch. 9 - A supersonic flow at M1=3,T1=285K, and p1=1atm is...Ch. 9 - Consider an infinitely thin flat plate at an angle...Ch. 9 - Consider a diamond-wedge airfoil such as shown in...Ch. 9 - Consider sonic flow. Calculate the maximum...Ch. 9 - Consider a circular cylinder (oriented with its...Ch. 9 - Consider the supersonic flow over a flat plate at...Ch. 9 - (The purpose of this problem is to calculate a...Ch. 9 - Repeat Problem 9.18, except with =30. Again, we...Ch. 9 - Consider a Mach 3 flow at 1 atm pressure initially...Ch. 9 - The purpose of this problem is to explain what...
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- Describe (i) Navier-stokes equation (ii) turbulent fluxarrow_forwardThe wave patterns of various delta w and delta k values are not same , even though the group velocity Vg is 1 for each wave pattern( due to delta w and delta k being equal to each other ) . Why are not all the wave patterns same ?arrow_forwardThe stream function for a progressive small-amplitude wave is psi = - H/2 g/sigma sin h k(h + z)/cosh kh cos (kx - sigma t) Draw the streamlines for t = 0, when T = 5 s, h = 10 m, and H = 2.0 m.arrow_forward
- Plot the streamlines and potential lines of the fl ow due to aline source of strength m at (a, 0) plus a source 3m at(2a, 0). What is the fl ow pattern viewed from afar?arrow_forwardhe complex potential of a line vortex of strength k centred on the origin is W=iklnz. Determine the complex potential of two line vortices of the same strength k , one located at the origin and one located at the point (x0,y0) . Show that at large distances, r≫r0=x20+y20‾‾‾‾‾‾‾√ , it reduces to the complex potential of a single vortex of strength 2k .arrow_forwardWater 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_forward
- The block of weight W = 50 N is pulled by a weight W0 = 60 N along the surface of a table by means of an inextensible cable and a pulley. Between the block and the table there is a uniform layer of oil of viscosity m = 0.1 Pa-s and clearance h = 2 mm. The contact area is 0.01 m2. Find the terminal velocity U if the table is very long.arrow_forwardA wave with a period T = 10 seconds is propagated shoreward over a uniformly sloping shelf from a depth d = 656 ft to a depth d = 9.8 ft. Find the wave celerities C and lengths L corresponding to depths d = 656 ft and d = 9.8 ftarrow_forwardQ. What is meant by the term “velocity of circulation” and explain its relevance in the quantity equation.arrow_forward
- Develop an equation for the transmitted wave height behind a vertical wall extending a depth d into the water of depth h, based on the concept that the wall allows the wave power below depth d to propagate past. Qualitatively, do you believe that your equation for the transmitted wave height will under- or overestimate the actual wave height ? Discuss your results.arrow_forwardAnswer: vp= 3745 mi/hrarrow_forwardDo gases usually have a constant specific weight? What increases in altitude is necessary in the stratosphere to halve the pressure? Assume a constant temperature of -56°C and the gas constant, R=287J/Kg/K. Write down the continuity law for compressible fluids. Describe the streamlines around a wing-shaped body. State the three characteristics of each of the following flows Laminar Turbulentarrow_forward
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