1. Using the Second and Third-Order Approximations, find the pressure acting on the upper and lower surfacesof a flat plate inclined at an angle of 10° toward the airflow at initial Mach number of 2 and freestreampressure of 1 atm.

Answered: Image /qna-images/answer/4bea31f2-5fe7-4853-a714-0fc9f8286264.jpg

Answered: 1. Using the Second and Third-Order…

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

Similar questions

4. It is important to remember that the isentropic relations and normal shock relationsare monotonic with Mach number and can be inverted. To illustrate this, consider thefollowing problems, (c) If the temperature jumps from 0 Celsius ahead of a shock to 200 Celsius behinda shock, what is the shock Mach number?(d) If the velocity behind a Mach 5 shock wave is 200 m/s, what is the upstreamvelocity?
1. Find the pressure of air at a point in a stream where M equals 1.8 when the pressure and Mach number at another point in the stream are 25 psia and 0.8 respectively. Assume isentropic conditions. 2. Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number of 1.6. Find the static pressure, density, and temperature at this Mach number. 3. Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure , temperature, and density. 4. A supersonic nozzle is a convergent-divergent duct , which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10atm and 550°R , respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume the flow is isentropic and , of course, compressible. 5.…
60. Find the Mach no. of an aircraft flies with the same Mach no. at elevations of 8600m (T =- 54 C°) and 11600 m (T = – 61 C°), if the aircraft flies 10% slower at 11600 m altitude. Joli s das
Ahead of the normal shock wave, the upstream pressure, temperature, and Mach number are O.53 atm, 255 K, and 2.8, respectively. Determine the Mach number downstream of the shock wave.
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 × 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.
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.
A normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?
Q3/ Steam at 500 kPa and a quality of 90 percent occupied a rigid vessel of volume 0.3m'. Calculate the mass, internal energy, and enthalpy of the steam.
Air enters a 5-cm-diameter duct at Mach number = 0.2, a temperature of 550 K and a pressure of 200 kPa. The average friction factor for the duct is 0.016. If the Mach number at the duct exit is 0.8, determine the pressure at the duct exit. (For air constant R = 287 J/kg.K, specific heat ratio K = 1.4). Select one: a. 65.95 kPa b. 54.85 kPa c. 80.75 kPa d. 47.27 kPa
Question : Air undergoes isentropic compression from the initial temperature and pressure T1 = 25°C and P1 = 100 kPa to the final pressure P2 = 500 kPa. Find the final temperature T2 (in Celsius). Justify your answer and show your work
The pressure at a point on the wing of an airplane is 75.8kPa. The airplane iswying with a velocity of 157 miles per hour at a condition associated to standard altitude of 3280 yards. Calculate the pressure coefficient at this point on the wing. b. After a while, the airplane's Mach number is increased to 0.5, compute for the Cp. a.
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

SEE MORE QUESTIONS

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS

1. Using the Second and Third-Order Approximations, find the pressure acting on the upper and lower surfaces of a flat plate inclined at an angle of 10° toward the airflow at initial Mach number of 2 and freestream pressure of 1 atm.