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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
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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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.
Transcribed Image Text: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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