5. Airflow at Mach 2 passes through an oblique shock as shown and deflects 10°. A second obliqueshock 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 regionsbounded by the shocks and that y = 1.4.Reflected oblique shock10°M=2

Answered: 5. Airflow at Mach 2 passes through an…

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

The instrument fairing on an aircraft is shown below, consisting of a forward ramp at30◦, a horizontal section, and a rear ramp at 25◦. During a flight in air at Mach 5.5,the static pressure is 42.6 kPa and the static temperature is 250 K. An oblique shockforms at the turn of the forward ramp, two expansion fans form at the front and rear ofthe horizontal section, and a second oblique shock forms at the turn of the rear ramp. (a) Calculate the Mach numbers and pressures at regions 2, 3, 4, and 5. (b) Determine stagnation pressure ratio p05/p01. (c) Tabulate the angles of all oblique shocks waves leading/trailing expansion waves relative to horizontal (not relative to flow angle). Gamma = 1.4, R=287 J/kgK PLEASE SHOW ALL WORK
The 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.
This year's qualification round featured a spaceship escaping from a shock wave (Problem B). The crew survived and wants to study the shock wave in more detail. It can be assumed that the shock wave travels through a stationary flow of an ideal polytropic gas which is adiabatic on both sides of the shock. Properties in front and behind a shock are related through the three Rankine-Hugoniot jump conditions (mass, momentum, energy conservation): Pivi = P2V2 Pivi + P1 = p2u3 +p2 + h2 + hị = 2 where p, v, p, and h are the density, shock velocity, pressure, and specific enthalpy in front (). and behind (2) the shock respectively. Shock front v2, P2; P2, h2 V1, P1, P1, h1 (a) Explain briefly the following terms used in the text above: (i) stationary flow (ii) polytropic gas (iii) specific enthalpy (b) Show with the Rankine-Hugoniot conditions that the change in specific enthalpy is given by: P2 - Pi 1 Ah = 2 P1 P2 The general form of Bernoulli's law is fulfilled on both sides of the shock…
4. Determine the upstream Mach number, considering an oblique shock wave with ew = 32° and a pressure ratio, P2/P1 = 3.0.
4. What is the limit of density change across a Normal shock wave in perfect gas. P2_ Y +1 lim M1-00 PI Y - 1
d*, 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.
An explosion occurs which creates a plane normal shock wave propagating into a region of air that is at rest (stagnation pressure po=1.0135×105Pa) and (stagnation temperature of To=290K). The speed of the shock is 1700 m/s. The air is modelled as an inviscid fluid, specific heat ratio γ=1.4 and gas constant R=287~J/kg⋅K. Calculate the air speed in m/s, relative to a stationary observer in the region behind the shock?
A 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. =
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.
Air at V_1 = 800 m/s, p_1 = 100 kPa, and T_1 = 300 K passes through a normal shock. Calculate the velocity V_2, temperature T_2, and pressure p_2 after the shock. What would be the values of T_2 and p_2 if the same velocity change were accomplished isentropically?
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
The pressure ratio across a normal shock wave that occurs in air is 1.25. Ahead of the shock wave, the pressure is 100 kPa and the temperature is 15 C. Find the velocity, pressure, and temperature of the air behind the shock wave.

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