n For isentropic air flowing through a converging-diverging nozzle, complete the tences below using increase or decrease: 1- When the air enters the nozzle with subsonic flow, as upstream cross-sectional area decrease, air velocity will 2- When the air enters the nozzle with supersonie flow, as upstream cross-sectional area decrease, air velocity will 3- When the air enters the throat with subsonic flow, as downstream cross-sectional area increase, air velocity will 4- When the air enters the throat with critical flow conditions, as downstream cross- sectional area increase, air velocity will 5- As nozzle critical area decrease, maximum mass flow rate of air will K exnands

n For isentropic air flowing through a converging-diverging nozzle, complete the tences below using increase or decrease: 1- When the air enters the nozzle with subsonic flow, as upstream cross-sectional area decrease, air velocity will 2- When the air enters the nozzle with supersonie flow, as upstream cross-sectional area decrease, air velocity will 3- When the air enters the throat with subsonic flow, as downstream cross-sectional area increase, air velocity will 4- When the air enters the throat with critical flow conditions, as downstream cross- sectional area increase, air velocity will 5- As nozzle critical area decrease, maximum mass flow rate of air will K exnands

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

Air flows isentropically at a rate of 1.3 kg/s from a large chamber through a convergent- divergent duct and leave to the outlet at Mach number 2.72. The air velocity, pressure OUTM EXAMINATION SESSION 2020/2021 (a) Sketch the system and label all components with subsonic/supersonic and UTM N 2020/2021 TM FINAL EXAMIN 2020/2021 answer. 2020/2021 st TION STAL EXAMINATION SEMESTAR I, SESSJO , SESSIOVON 3, SERIONON Esto ON b/202 2020/202 and temperature at a location somewhere along the system were found to be 900 m/s, OUTM 150 kPa and 60°C, respectively. FINAL EXAMINATIC SEMESTER IL SESSION 2025/202 RATION 2020/2021 FINAL EXAMINA BEMENTER I SESSION 2020/202 diffuser/nozzle according to the effect of area change. Justify your ALE eSTER R, SESSION 202b/202 (b) Determine the pressure and temperature of the air in the large chamber, the area at throat, and the velocity at outlet. zb/202
For supersonic and hypersonic wind tunnels, a diffuser efficiency, ηD,can be defined as the ratio of the total pressures at the diffuser exit andnozzle reservoir, divided by the total pressure ratio across a normal shockat the test-section Mach number. This is a measure of the efficiency ofthe diffuser relative to normal shock pressure recovery. Consider asupersonic wind tunnel designed for a test-section Mach number of 3.0which exhausts directly to the atmosphere. The diffuser efficiency is 1.2.Calculate the minimum reservoir pressure necessary for running thetunnel.
P Flag question For an ideal gas if the specific internal energy at a specific pressure and temperature of 20 °C is u=123.8 kJ/kg, what is the specific internal energy if the pressure is doubled while the temperature stays the same. Soloot ond
What is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?
-NES Start from first principle to show that, for perfect gas the velocity of the sound is given by: C= √KRT
The pressure of steam 400 C and u = 2949 kJ/kg is most nearly
aircraft flies at the same Mach number but 50 m/s slower at 8 km compared to its speed at sea level. Find this Mach number a. 1.45 b. 1.55 c. 2.25 d. 1.65 e. 2.50.
What is the Mach Number of an air with a velocity of 250 m/s, at a temperature at 2800 meters?
Air at 30 lbf/in2 absolute and 200F flows from a reservoir into a duct. The flow is steady, adiabatic, frictionless. The flow rate is 10lbm/s. What are the cross-sectional area, temperature, pressure, and Mach number at the point in the duct where the velocity is 1,400 ft/s?
3. Heat Loss from Longitudinal Fin. A longitudinal aluminum fin, as shown in Fig. 15.8-3a (k = 230 W/m K), is attached to a copper tube having of 0.04 m. The length of the fin is 0.080 m and the thickness is 3 mm. The tube base is held at 450 K and the external surrounding air at 300 K has a convective coefficient of 25 W/m2 K. Calculate the fin efficiency and the heat loss from the fin per 1.0 m of length. an outside radius AM .a
For oblique shock, the downstream * Mach number is always less than unity may be less or more than unity O is always more than unity can never be unity O is parallel to shock wave O is normal to shock wave O O O O O O
The values of Cp for the consu Ammonia in air is a toxic mixture when the ammonia is 0.45% by volume. Calculate how much leakage from an ammonia compressor can be tolerated per 1000m³ of space. The pressure is 1bas and the temperature is 15 °C. The molar mass of ammonia (NH3) is 17kg/kmol, and it may assume to act as a perfect gas in this case. and 70 °C. The vessel is A perfect insulated vessel having three compartments A, B and C of volume 1.3m³, 1.2 m³ and 1.0 m² respectively are separated from each other by thin membrane. Compartment A is filled with ritrogen having a pressure 3bar, at a temperature 25 °C, compartment B is filled with hydrogen having a pressure of 20bar at a temperature -40 °C and compartment C filled with carbon (IV) oxide at a temperature 175 °C and pressure 6bar. If the thin membrane are punctured and the three gases allowed to mix freely, calculate: (i) The final temperature of the mixture The final pressure of the mixture (iii) The change in entropy of the…