1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 x 10° N/m? and 0°C, determine the static and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge angle. pressure

1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 x 10° N/m? and 0°C, determine the static and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge angle. pressure

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Related questions

Q: A piston moves along a tube containing air at an initial sound speed of 330 m/s. When the piston…

Q: Determine the Mach number at section 2. Express your answer using three significant figures. 195]…

A: To find:the Mach number.

Q: Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5…

A: Pressure = 5 atm Temperature = 500 K Exit mach number = 3 Value taken Specific heat ratio = 1.4…

Q: 1. Using the Second and Third-Order Approximations, find the pressure acting on the upper and lower…

Q: The static pressure to stagnation pressure ratio at a point in a gas flow field is measured with a…

A: From the data given in question, Ratio of specific heat for air = γ = 1.4

Q: verging-diverging nozzle of ave occurs at the exit plane

A: Determine the value of pressure and temperature before the shock.

Q: Consider a hypersonic vehicle with a spherical nose flying at Mach 20at a standard altitude of…

A: Given Data: The ambient temperature is T∞=500°R. The ambient pressure is P∞=3.06 lb/ft2. Nose…

Q: A jet-propelled airliner flies at an altitude of 15,000 m and a velocity of 265 m/s. What is the…

A: Given:The jet flies at an altitude of The velocity of flight, The airflow to each engine at zero…

Q: Air flows at 200 m/s through the pipe. The temperature is 500 K and the absolute stagnation pressure…

Q: When a pitot-static tube is placed in a supersonic flow, the probe reads P = 190 kPa and P = 150…

A: Given data:To determine:Freestream mach number and velocityThe Mach number inside the shock can be…

Q: The pressure upstream of a normal shock wave is 1 atm. The pressureand temperature downstream of the…

A: Given data: Upstream pressure of a normal shock wave = 1 atm Downstream pressure…

Q: A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnation…

A: Given Data: M1 = 3.8 P = 5Mpa T = 1100K v2-v1 = 23o To find: 1) Downstream Mach 2) Downstream…

Q: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

A: Given data: Initial upstream pressure, P1 = 1 atm. From the standard air properties, the specific…

Q: The Mach number behind a normal shock wave is 0.4752. What is the Mach number in front of the wave?…

A: the Mach number in front of the wave…

Q: Q11: Air enters the converging section shown in Figure and a normal shock occurs at the exit. The…

Q: (3.b) A converging-diverging nozzle is designed to expand air from a chamber in which the pressure…

A: “Since you have posted a question with multiple sub-parts, we will provide the solution only to the…

Q: Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over a wedge which…

Q: l answer should be correct

Q: QUESTION 14 The fan of a turbofan engine is tested at high speed. The flow approaches the fan tip at…

A: Given: The mach number of floe approaching fan, M1, ref = 1.19 The shock angle, β = 87° For air, n =…

Q: A Boeing 747 cruises at a Mach number of Ma=0.87 at an altitude of z = 13 km on a standard day. A…

A: Given that, Mach number at an altitude,Ma1=0.87,h1=13 km,The cabin is pressurized to an equivalent…

Question

1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An
oblique shock, making an angle of 40° with the flow direction, is
attached to the wedge. If the static pressure and temperature in the
freestream are 0.5 x 10 N/m2 and 0°C, determine the static pressure
and temperature behind the wave, the Mach number of the flow passing
over the wedge, and the wedge angle.

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1

Step 2

Step 3

Step 4

Trending now

This is a popular solution!

Step by step

Solved in 4 steps

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

The velocity ratio(v1/v2)of an isentropic flow through a supersonic wind tunnel is 0.915 ifthe velocity and mach number at the exit are 376.95 m/s and 2.60 respectively find the value of speed of sound at the entrance
Stagnation pressure and temperature probes are located on the nose of a supersonic aircraft. At 35,000 ft altitude a normal shock stands in front of the probes. The temperature probe indicates T0 = 420F behind the shock. Calculate the Mach number and air speed of the plane. Find the static and stagnation pressures behind the shock. Show the process and the static and stagnation state points on a Ts diagram.
Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over a wedge which deflects the flow by 15°, as shown in the figure. If the pressure and temperature in the uniform flow are 40 kPa and 263 K, respectively, determine the shock wave angle, Mach number, pressure and temperature downstream of the oblique shock wave. Oblique Shock Wave M = 2.5 15° T= 263 K P = 40 KPa
In the test section of a supersonic wind tunnel, a Pitot tube in the flowreads a pressure of 1.13 atm. A static pressure measurement (from apressure tap on the sidewall of the test section) yields 0.1 atm. Calculatethe Mach number of the flow in the test section.
Air flows at 200 m/s through the pipe. The temperature is 500 K and the absolute stagnation pressure is 200 kPa. Assume isentropic flow. For air R = 286.9 J/kg · K] and k = 1.40. (Figure 1) 0.3 m Determine the Mach number of the flow. Express your answer using three significant figures. M = Determine the mass flow. Express your answer using three significant figures. m = kg/s
Problem 3. A Pitot tube is placed in a supersonic wind tunnel where the temperature is T = 300 K and the Mach number is Max = 2.0. A normal shock stands in front of the probe. Behind the shock, the pressure jumps to py = 40 kPa. (a) Find the pressure, velocity, and density upstream of the shock. (b) Find the stagnation temperature and stagnation pressure before and after the shock. (c) Show static and stagnation points and process path on a T-s diagram and briefly describe the process.
What is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?
The Pitot tube on a supersonic aircraft (see the Video) cruising at an altitude of 25000 ft senses a stagnation pressure of 15.0 psia. If the atmosphere is considered standard, determine (a) the Mach number of the aircraft, (b) the airspeed. A shock wave is present just upstream of the probe impact hole. (a) Ma = (b) V= ft/s
2. = Air enters a constant-area duct at Mach 3 and stagnation conditions 750 K and 1.3 MPa. Assume y 1.4. In the duct it undergoes frictionless heating such that the exit Mach number is unity. Consider two cases: (a) normal shock at the inlet of the duct and (b) shock-free supersonic heating. Determine the stagnation temperature and pressure at the exit in each case. Is there any reason why the total energy transfer should differ (or be equal) in the two cases?
A jet transport is flying at a standard altitude of 30,000 feet with a velocity of 550 miles per hour. What is the Mach number?
Consider a hypersonic vehicle with a spherical nose flying at Mach 20at a standard altitude of 150,000 ft, where the ambient temperature andpressure are 500◦R and 3.06 lb/ft2, respectively. At the point on thesurface of the nose located 20◦ away from the stagnation point, estimatethe: (a) pressure, (b) temperature, (c) Mach number, and (d) velocity ofthe flow.
A P-51 Mustang is traveling at 24000 ft altitude. The inlet air temperature is 5 degrees C. Calculate the speed of sound (in m/s) in the intake port. If the average Mach Number of the intake port is 0.46, what is the speed of the intake airflow?