velocity behinel the waveQ- A normal shock wave oves at alonstuint velocity of542 mis înto Still air with atemperatune and pressune of352 K and 120 kpa vespectively Determive theStacknete Stutic and Stagnurion Gemeehitit coneditions presentin the arr after the Passage of the Wave as Well as theTx=352 KBUS=542 m'sPx= 120

Answered: Image /qna-images/answer/2cdc5d0b-6415-4ccc-a3b6-01e766d474d4.jpg

Ya A normal Shock wave moves at alonstuint velocity of 542 mis into Still air with atemperatune and pressune of 352K and 120 kpa vespectively Determine the Stackete Studic and Stagnution Gemehitit conclitions presont in fhe arr after the passage of the waue as Well as the velocity behinel the wave Tx= 352 K Bus= ち42 mls Px= l20 111.t

Ya A normal Shock wave moves at alonstuint velocity of 542 mis into Still air with atemperatune and pressune of 352K and 120 kpa vespectively Determine the Stackete Studic and Stagnution Gemehitit conclitions presont in fhe arr after the passage of the waue as Well as the velocity behinel the wave Tx= 352 K Bus= ち42 mls Px= l20 111.t

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 is supplied to a The throat area of the converging-diverging nozzle from a tank where the temperature is 400 K. converging-diverging nozzle is and 0.01 m² and the mass flow rate through the nozzle is 3.5 kg/s. The medium into which the nozzle discharges is at a pressure of 100 kPa. A normal shock wave is located at the diverging part of the nozzle and the velocity at the exit of the nozzle is 200 m/s. Assuming adiabatic and frictionless flow, determine a) the Mach number upstream of the shock wave and b) the area at which the shock wave is located. T = 400 K At = 0.01 m² e p = 100 kPa V₂ = 200 m/s
Air at a dry ball temperature of 9m5 ° and rh 4% is passed over the cooling coil so that the temperature of the dry ball of air becomes 50 ° C. How much heat is released from the air in the process
4
I need the answer quickly
sing eneray balene for a clesed ayntom and colel J madels cnd ncele ting chenses in kine tie chd Peta tial energies Anscuer the folbowing, (Rave ing fabaula) 0-2 ky of air (mdel on on ideed gou ) Undeges as sothermael beacase in- d- Piston- Cyledex o4ssably.during which the dir f looka . An the brocee s the velame occubicl oh decieves eneray by d hat trofer by dir incdeadey twice Va =N, - 4. Defeamine dir tenpte tuse during abocaes in k? prassuse during this dir ploces (Anco deco dos nt chage ) why ? Teachers Signature:.
I need help answering questions 4, 5, and 6 pertaining to the print provided below.
It's a complete question. Need help asap.
A piston confined in a tube is suddenly accelerated to a velocity at (m/s) which causes a 구2 shock wave if the temperature of the air is 2C). Solution:
Air at 290°K and 105 P a approaches a normal shock. The temperature downstream of the shock is 540°K. Find: (a) The velocity downstream of the shock. (b) The pressure change across the shock, and compare it with that calculated for an isentropic flow with the same deceleration.
A con area of o.0052r venging-diverg ing nozzle with a th voat D attached to Very lange tank of air in which the pressure 's 136 k pa and temperatune is 67 C O-00 The nozzle exhaupt to atmosphene With a pressune of l05 kpa-if the meess- flow vate is (2 kys)• Jerermine the exik and Mach noutber num ber' at the throat- The flow in the hozle is isenaropic Po:136 Ken Pbsl05Kpy To z67 C
A
Air flows isentropically from a large reservoir maintained at 597°C and 1.0 MPa absolute into a converging-diverging duct. The flow at the exit plane of diverging duct is supersonic. The duct is 2 m long and has a circular cross sectional area with radius, r in m that varies in axial distance, x along the duct that is defined by r = 0.03x² +0.02 where x extends from -1.0 m to 1.0 m. (a) Sketch a 2D diagram of the above system on a graph of duct radius against axial distance with appropriate labelling. (b) Using the isentropic table provided, determine (i) the Mach number, pressure and temperature at the exit plane, and (ii) the mass flow rate through the duct. E.Q2 (c) If the radius of the duct as specified in E.Q2 is doubled, would the Mach number on the exit plane be increased, decreased or remain unchanged? Explain your answer briefly. Take heat specific ratio of 1.4 and specific gas constant of 0.287 kJ/(kg-K) for air.