Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.4P
Consider an oblique shock wave with a wave angle of
a.
b.
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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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- For a moving normal shock wave the gas velocity represents the y-velocity when the normal shock wave was stationary True Or flasearrow_forwardThe flow just upstream of a normal shock wave is given byp1 = 1800 lb/ft2, T1 = 480 ◦R, and M1 = 3.1. Calculate the velocity andM∗ behind the shock.arrow_forwardd*, 2. Consider a normal shock wave in air where the upstream flow properties are u1 = 690 m/s, T1 = 288 K, and p1=1 atm. Calculate the velocity, temperature, and pressure downstream of the shock.arrow_forward
- Constant density and non-viscuous fuid. turbulent static ideal isothermalarrow_forwardPlease answer fastarrow_forwardA normal shock wave propagates into atmosphere where the atmospheric temperature is equal 336K and pressure is 0.8 atm. For a given pressure ratio of p2/p₁ 41 to T₁ = a) Assuming stationary atmosphere, calculate the shock wave velocity and the velocity induced behind the shock wave. Also calculate the temperature, total pressure and total temperature of the fluid particles behind the shock wave using equations for moving normal shock. =arrow_forward
- 5. Airflow at Mach 2 passes through an oblique shock as shown and deflects 10°. A second oblique shock reflects from the solid wall. What is the pressure ratio (p3/p₁) across the two-shock system? Assume that there is no boundary layer near the wall, so the flow is uniform in each of the regions bounded by the shocks and that y = 1.4. Reflected oblique shock 10° M=2arrow_forwardThe entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1)arrow_forwardPlease draw and label the diagram correctly.arrow_forward
- The driver and driven gases in a shock tube are both air at 300 K. Assume p4/p1 = 8.006. After the diaphragm is broken, an incident shock wave is propagating into the driven section and an incident expansion wave is propagating into the driver section. If the strength of the incident shock (p2/p1) is 2.6, a. Calculate the strength of the incident expansion wave (p3/p4). b. Calculate the induced mass motion velocity behind the expansion wave. c. Find the propagation velocity of the head expansion wave. d. Find the propagation velocity of the tail expansion wave.arrow_forward1. A normal shock wave with a velocity of 700 m/s moves down a tube into air with static properties of 40 kPa and 320 K. At the end of the tube, a piston is moving at 60 m/s, as shown below. Find the velocity of the reflected wave and the static and stagnation pressures (relative to the tube) behind the reflected wave. Vw= 700 m/s V = 60 m/s P = 40 kPa T= 320 Karrow_forwardThe flow just upstream of a normal shock wave is given by p1 = 1 atm,T1 = 288 K, and M1 = 2.6. Calculate the following properties justdownstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change inentropy across the shock.arrow_forward
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