A solid propellant rocket motor was tested at sea level and following data were obtained: Propellant burn time = 34 sec Initial mass before test = 1400 kg Mass after test = 320 kg Average thrust = 85,000 N Chamber pressure = 8.0 MPa Nozzle exit pressure = 0.08 MPa Atmospheric pressure = 0.1013 MPa Nozzle throat diameter = 0.093 m %3D %3D %3D %3D %3D Nozzle exit diameter = 0.312 m Calculate: (1) Mass flow rate m; (2) Exit velocity v2; (3) Characteristic velocity c*; (4) Effective exhaust velocity c; and (5) Specific Impulse I, at sea level. Draw the sketch of Chamber & Nozzle, and Show all calculations.

A solid propellant rocket motor was tested at sea level and following data were obtained: Propellant burn time = 34 sec Initial mass before test = 1400 kg Mass after test = 320 kg Average thrust = 85,000 N Chamber pressure = 8.0 MPa Nozzle exit pressure = 0.08 MPa Atmospheric pressure = 0.1013 MPa Nozzle throat diameter = 0.093 m %3D %3D %3D %3D %3D Nozzle exit diameter = 0.312 m Calculate: (1) Mass flow rate m; (2) Exit velocity v2; (3) Characteristic velocity c*; (4) Effective exhaust velocity c; and (5) Specific Impulse I, at sea level. Draw the sketch of Chamber & Nozzle, and Show all calculations.

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

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Question

A solid propellant rocket motor was tested at sea level and following data were obtained:
Propellant burn time = 34 sec
Initial mass before test = 1400 kg
Mass after test = 320 kg
Average thrust = 85,000 N
Chamber pressure = 8.0 MPa
Nozzle exit pressure = 0.08 MPa
Atmospheric pressure = 0.1013 MPa
Nozzle throat diameter = 0.093 m
Nozzle exit diameter = 0.312 m
Calculate: (1) Mass flow rate m; (2) Exit velocity v2; (3) Characteristic velocity c*;
(4) Effective exhaust velocity c; and (5) Specific Impulse I, at sea level.
Draw the sketch of Chamber & Nozzle, and Show all calculations.

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