Answered: An air stream, with T1 =0 C, p1 = 60.0…

An air stream, with T1 =0 C, p1 = 60.0 kPa (abs), and V 497 m/sec, undergoes a normal shock. Determine the Mach number, speed, and stagnation pressure downstream from the shock. %3D

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 uniform supersonic airflow traveling at Mach 2.0 passes over a wedge (Fig. 10E.1). An oblique…

A: supersonic air flow travelling at passes over a wedge,T1=-10o CT1=263.15 KFrom table at Mach,…

Q: Air is flowing in the converging-diverging nozzle shown in the figure below. - A = 15 cm² Shock A₁ =…

A: To findDetermine the three critical pressure ratios.Determine the Mach number immediately upstream…

Q: Q9: A normal shock wave is propagated into sti air with a velocity of 722.4 m/s. The still ai…

A: Given-Data:-V=722.4m/sP1=1atm=1.0133×105N/m2T1=294.4K To-Find:- 1) Mach number2) Pressure 3)…

Q: Q5: air velocity decrease from 480m/s chrough the shock. If the pressure and density upstream of the…

Q: Air at 200 kPa, 100 °C, and Mach number Ma=0.8 flows through a duct. Calculate thevelocity, the…

Q: Determine the critical mach number according to linear theory

A: Given Local mach number, MA = 0.435 Streamline mach number, M0 = 0.3 Find Critical mach…

Q: Q.5. With careful design, one can orient the bend on the lower wall so that the reflected wave is…

A: Please find the solution below

Q: We are given the pressure on one side of a normal shock wave is 1 atmosphere, and the pressure and…

A: given Px = 1atm Py = 10 atm , Ty = 775K

Q: A supersonic inlet is sketched below and contains an oblique shock wave followed by a normal shock…

A: Given:M1=3T1=300 KP1=101.3 KPa

Q: A flow undergoes a normal shock just past a section where the area is 53 cm²: p= 12 kPa, p = 0.182…

Q: This year's qualification round featured a spaceship escaping The crew survived and wants to study…

A: Space Wave :- It is a type of propogating disturbance that moves faster than the local speed of…

Q: What is the Mach of airflow with 150 m/s at a pressure of 0.95 atm and a Density of 1.15 kg/m^3?

Q: 5. At 30000ft, estimate the magnitude of transonic drag rise. Using this estimate, calculate the…

A: Where terms followdM- magnitude of transonic drag riseM1- Mach numberMDD- Drag-divergence Mach…

Q: Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air…

A: To calculate the mass flow rate of air through the nozzle, we can use the continuity equation, which…

Q: Air at V_1 = 800 m/s, p_1 = 100 kPa, and T_1 = 300 K passes through a normal shock. Calculate the…

A: Dear Students

Q: An air formed a shockwave with a Mach of 2.3. What is the pressure downstream when the pressure…

A: Write the expression for the static pressure before the normal shock. Here, ρ represents the…

Q: At a point in the flow over an F-15 high-performance fighter airplane, the density,temperature and…

A: Please go through the below answer. This is the second time I'm answering this questionExplanation:

Q: A normal shock wave exists in air flow with up stream M=2, and a pressure of 20 kpa and temperature…

A: M1=2 , and P1=20 kPa T1=15°C M1=V1γRT1V1=M1×γRT1V1=2×1.4×287×288V1=680.34 msec Now…

Q: Problem 1: The inlet of a jet engine flying at supersonic speed (M∞ > 1) is supposed to compress…

A: Given data:Inlet area = AiThroat area = A*Area ratio= 1.3and, throat is always sonicThe objective of…

Q: A fuel–air mixture, assumed equivalent to air, enters a ductcombustion chamber at V1 = 104 m/s and…

A: Given: The initial temperature,T1 300 K The initial velocity, V1=1.4 m/s Solution:

Q: 56. A supersonic aircraft flies with a velocity greater by 39 m-s1 at 7600 m elevation, (T = - 51 C°…

Q: Air flows in the channel in the figure below. The pressure at station 1 is 59 psia. Determine the…

A: Given data:

Q: 15. Determine the aircraft Mach no. flies with the same Mach no. at elevations of 8100m (T=-44 C°)…

A: The Mach number of the flight at 8100 meters can be expressed as,

Q: Q9: A normal shock wave is propagated into still air with a velocity of 722.4 m/s. The still air…

A: "Since you have posted a question with multiple sub-parts, we will solve first three sub parts for…

Q: The Pitot tube on a supersonic aircraft (see the Video) cruising at an altitude of 25000 ft senses a…

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: At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a…

A: To findthe Mach number involved.the instantaneous location, I, of the point source.Giventhe radius…

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

A: Given data as per the question Mach number behind a normal shock wave = 0.4752 mach no. behind the…

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: Determine the critical mach number according to linear theory

A: Given Local mach number, MA = 0.435 Streamline mach number, M0 = 0.3 Find Critical mach…

Q: 6. A certain deflection angle in a supersonic stream with a Mach number of 2.2 and a pressure ratio…

A: A dimensionless quantitity which is the ratio between the velocity of the object to tevelocity of…

Q: Consider a normal shock wave at sea level with the density ratio, p2/p1 = 2.67. What are the…

A: A normal shock occurs when the shock wave is perpendicular to the flow direction. If the flow is…

Q: Air enters a rectangular duct at T1 = 285 K, P1 = 390 kPa, and Ma1 = 2. Heat is transferred to the…

A: The static temperature at the inlet of the duct is T1=285 K. The inlet pressure of the duct is…

Q: f density change across a Normal shock

A: Detailed Solution given below

Q: If the back pressure is low enough and the throat is sonic, the Mach number is more than I in a/an…

A: Solution: Mach number variation with area can be given by the relation,…

Q: A perfect gas (y = 1.4) enters a converging-diverging nozzle with a Mách number of 0.50 and local…

A: gama =1.4 inlet mach number (M1) =0.5 Inlet velocity (V1) = 165 m/s P1 =280 KPa T1 = 280 K Throat…

Q: Q1. A turbojet aircraft flying at speed of 1645 km/h and altitude of 9000 m. A supersonic intake was…

A: Given: The turbojet speed, v = 1645 km/h The turbojet altitude, h = 9000 m The deflection of conical…

Q: 1. Air (y=1.4) enters a converging-diverging nozzle from a reservoir which is at a pressure of 300…

Question

An air stream, with T =0 C, p1= 60.0 kPa (abs), and V = 497 m/sec, undergoes
a normal shock. Determine the Mach number, speed, and stagnation pressure
downstream from the shock.
%3D

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

VIEW

Step 2

VIEW

Trending now

This is a popular solution!

Step by step

Solved in 2 steps with 2 images

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

QI: If the combined moment of the two forces about point C is zero, determine (a) The magnitude of the force P (b) The magnitude R of the resultant of the two forces, Specify the distance x from point O to the point on the x-axis through which the line of action of R passes. 120N 40 mm +P 40 mm 60 40 mm
None
78. For an aircraft flies with the same Mach no. at elevations of 8800m (T = - 56 C°) and 11800 m (T =- 63 C°), if the aircraft flies 13% slower at 11800 m altitude, find the Mach no. of the aircraft.
Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 60.0 kPa (abs), T1 = 27°C, Vị = 486 m/s. At a downstream section 2, p2 = 78.8 kPa (abs). Determine: a. Mach number, Maz b. sketch geometry of the duct
Air flows into a converging duct, and a normal shock stands at the exit of the duct. Downstream of the shock, the Mach number is 0.54. If p2/p1 = 2, compute the Mach number at the entrance of the duct and the area ratio A1/A2.
V1
Air flows isentropically through a duct as shown in the figure below. For the conditions shown, find the Mach number at both stations 1 and 2 and the flowrate. The diameter is not necessarily constant. Ma₁ (1) D₁ = 0.15 m V₁ = 40 m/s P1 = 4 atm abs. Ma₁ = Ma₂ = i m₁ = M. kg/s Ma₂ (2 T₂ = 225 K P2 = 2 atm abs.
For low-speed (nearly incompressible) gas flow, the stagna- tion pressure can be computed from Bernoulli's equation: Po = P +pV² (a) For higher subsonic speeds, show that the isentropic relation (9.28a) can be expanded in a power series as follows: 2 -k Po -p+ pv*(1+ Ma' + Ma' + --) 24 (b) Suppose that a pitot-static tube in air measures the pres- sure difference p, - p and uses the Bernoulli relation, with stagnation density, to estimate the gas velocity. At what Mach number will the error be 4 percent?
Q6: Air following through constant area duct encounters stationary shock as shown in figure. Find the Mach number, temperature, pressure, stagnation pressure, stagnation temperature and velocity after the shock. Ans.: M2 = 0.6746, T2 = 344 K, p2 = 137 kPa, To = 375 K, po = 186 kPa. V1=500 m/s P;=50 kPa 1-250 K → (1) | (2)
3. Assume a supersonic flow with M=2, P=1 atm, and T=288 K that is deflected via 15° at a compression corner. Determine M, P, T, as well as PO and TO behind the associated oblique shock wave.
Problem 5. A Boeing 747 cruises at a Mach number of Ma = 0.87 at an altitude of z = 13 km on a standard day. A window in the cockpit is located where the external flow outside the window is at a Mach number of Ma = 0.2 relative to the plane surface (just outside the boundary layer). The cabin is pressurized to an equivalent altitude of z = 2.5 km for a standard atmosphere. (a) Estimate the pressure difference across the window and specify the direction of the net pressure force. (b) Sketch the stagnation pressure, static pressures, and critical pressure on a T-s diagram.
Nitrogen at 700 kPa pressure and 300K temperature enters a convergent divergent nozzle at negligible speed and passes through a normal shock wave at the Mach number of 3. Calculate the pressure, temperature, velocity, Mach number and stop pressure in the flow behind the shock wave. Compare the values you find with the values found with the air passing through the normal shockwave under the same conditions.