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A static thrust stand as sketched In the figure snown is used for testing a Jet engine. The following conditions are known for a typical test: the fuel enters at a fiow rate of S5 kg/s vith approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; ntake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 (kg. K). Control volume Fuel inlet Patrm P1 U2 Section (2) Section (1)

A static thrust stand as sketched In the figure snown is used for testing a Jet engine. The following conditions are known for a typical test: the fuel enters at a fiow rate of S5 kg/s vith approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; ntake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 (kg. K). Control volume Fuel inlet Patrm P1 U2 Section (2) Section (1)

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
Problem 1.1MA
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I want this question required 

A)The inlet air temperature in K is:

B)  The net linear momentum in kN is:

C)The exhaust gas density in kg/m^3 is:

D)The reaction force F_R in kN is:

E)The inlet mass flow rate in kg/s is:

F)The linear momentum at the exhaust in kN is:

G)The exhaust area in m^2 is:

H)The exhaust gas density in kg/m^3 is:

I)The exhaust mass flow rate in kg/s is:

J) The exhaust area in m^2 is:

A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/s with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 J/kg. K). Control volume Fuel inlet - P1 Section (2) Section (1)
Transcribed Image Text:A static thrust stand as sketched in the figure shown is used for testing a jet engine. The following conditions are known for a typical test: the fuel enters at a flow rate of 5 kg/s with approximate zero velocity. Intake air velocity is 215 m/s and exhaust gas velocity is 500 m/s; intake cross-sectional area is 1.2 m^2; intake static gauge pressure -30 kPa; intake air density is 0.9 kg/m^3 and exhaust static temperature 800 K; exhaust static pressure 0 kPa. If the atmospheric pressure is 100 kPa, the constant for air and gas is R= 287 J/kg. K). Control volume Fuel inlet - P1 Section (2) Section (1)
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