FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 9, Problem 9.9P
Consider an oblique shock generated at a compression corner with a deflection angle
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A 6° half-angle wedge creates the reflected shock system inFig. If Ma3 = 2.5, find (a) Ma1 and (b) the angle α.
Q.3. Airflow at M1 = 2.2 takes a compression turn of 12° and then another turn of
angle as shown in the figure. What is the maximum value of 0max for the second
shock to be attached?
%3D
M1 =
= 2.2
emax?
12°
Consider an oblique shock generated at a compression corner with adeflection angle θ = 18.2◦. A straight horizontal wall is present above thecorner, as shown . If the upstream flow has the propertiesM1 = 3.2, p1 = 1 atm and T1 = 520◦R, calculate M3, p3, and T3 behindthe reflected shock from the upper wall. Also, obtain the angle whichthe reflected shock makes with the upper wall.
Chapter 9 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
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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- = 1-An oblique shock forms in air at an angle of 0 30°. Before passing through the shock, the air has a temperature of 60°F, a pressure of 10 psia, and is traveling at M = 2.6. elocity components before and after (a) Compute the normal and tangential the shock. HEGE Of and (b) Determine the temperature and pressure after the shock. (c) What is the deflection angle?arrow_forwardQ.3. Airflow at M1 = 2.2 takes a compression turn of 12° and then another turn of angle as shown in the figure. What is the maximum value of 0max for the second shock to be attached? 3 M1 = 2.2 Omax (2 12°arrow_forward2. Determine the back pressure necessary for a normal shock to appear at the exit of a converging-diverging nozzle, as shown in the figure. Assume y = 1.4. Pr = 1.0 MPa T₁ = 800 K рь A exit A throat = 2.0arrow_forward
- In the figure below, M1 = 3.0 and A1 = 2.0ft?. If the fluid is carbon monoxide and the shock occurs at an area of 1.8ft?, what is the minimum area possible for section 4? What is the entropy generation across the shock?arrow_forwardThe flow downstream of intersecting shocks of opposite families (compression vs. expansion) adjusts itself such that the total pressures on either side of the slip line are equal and the flow directions match the pressure and velocity match on either side of the slip line the entropy on either side of the slip line is equal the pressures on either side of the slip line are equal and the flow directions matcharrow_forwardQ.3. Airflow at M1 angle as shown in the figure. What is the maximum value of 0max for the second 2.2 takes a compression turn of 12° and then another turn of shock to be attached? M1 = 2.2 Omax 12°arrow_forward
- 1. 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_forward30. A normal shock wave across which the pressure ratio is 1.25 is propagating down a duct containing still air at a pressure of 120 kPa and a temperature of 35°C. This shock wave is reflected off the closed end of the duct. Find the pressure and tem- perature behind the reflected shock wave.arrow_forwardA sample of steam is at a pressure of 300 kPa (x=0.75). Solve for its entropy.arrow_forward
- Q1. A turbojet aircraft flying at speed of 1645 km/h and altitude of 9000 m. A supersonic intake was designed with a conical center body, which generated one oblique shock wave and normal shock wave at the inlet of the aircraft. The deflection of the conical center body is a 10°. Calculate the fluid flow properties and velocity at the aircraft inlet of the intake. Assume a weak solution. Take: R= 0.287 kJ/kg K, and Cp=0.9 kJ/kg K.arrow_forward0/ QI diesel engine has a clearance volume is 0.00025m and bore and stroke of 152.5mm and 200mm, respectively. A charge of air at 100kPa and 20C is taken into the cylinder and compressed adiabatically y=1.4. After combustion at constant pressure the temperature is 1090°C. The expansion which follows is adiabatic. Find a- the temperature and the pressure at the end of compression b- the temperature and pressure after expansion c- the ideal thermal efficiency of the engine (591°Č,4400kPa,227°C,188kPa,0.633)arrow_forwardTwo gases enter a combining tube and leave as a single mixture. . For the first gas, A₁=72in² V₁=205m/s V₁=120gal/lbm . For the other gas, A₂=48in² m2=20lbm/s P2=2kgm/m³ ● . At the exit, V3=320ft/s V2=9ft³/lbm Find the (a) velocity at section 2 in m/s, (b) mass flow rate at the exit section in kgm/s, and (c) area at the exit section in m².arrow_forward
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