- #1
JRS192
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- 0
Hi,
I hope that, given I've sourced what I can, you may be able to help? I'm Currently working on a lab report for my Aeroengines unit based on Convergent-Divergent nozzle (http://imgur.com/HQML2Au).
From the drawing, I have been provided D1, D2, D3, D4, T1, T2, T3, T4, P1, P2, P3, Velocity, Ambient Pressure and Ambient Temperature.
I need to calculate the following:
- Mass Air Flow rate through the system at each inlet valve.
- Velocity at each section (inlet, throat, exit) of the nozzle.
- Speed of Sound at each section (inlet, throat, exit) of the nozzle.
- Mach No. at each section (inlet, throat, exit) of the nozzle.
I don't have a real grasp of this subject, but from some text-books I've figured out the following, and mainly, I just want to ensure what I'm doing is correct.
•Mass Flow Rate
Density x Surface Area x Velocity Density = pRT, so I assume I'd take P1, and divide by (T1 x Universal Gas Constant)
Surface Area = (Pi x D12)/4
Velocity = Provided as part of the experiment.
Velocity
Continuity Equation = p1A1V1=p2A2V2 Now that I have p1 and A1 from the previous part, I should be able to rearrange to get V1? I'm assuming this would be the same for V3, V4?
Speed of Sound
I have this for a perfect gas: a = ROOT(yGcRT) So Root(specific heat ratio(?) x Newton's Constant x Gas Constant x Temperature?)
Not sure how to calculate each part of this
Mach No. M2 = V2/(specific heat ratio(?) x Newton's Constant x Gas Constant x Temperature?)
Any help at all would be appreciated, I've worked out what I can, as I don't want to flat-out ask for answers...
Thank you! :)
I hope that, given I've sourced what I can, you may be able to help? I'm Currently working on a lab report for my Aeroengines unit based on Convergent-Divergent nozzle (http://imgur.com/HQML2Au).
From the drawing, I have been provided D1, D2, D3, D4, T1, T2, T3, T4, P1, P2, P3, Velocity, Ambient Pressure and Ambient Temperature.
I need to calculate the following:
- Mass Air Flow rate through the system at each inlet valve.
- Velocity at each section (inlet, throat, exit) of the nozzle.
- Speed of Sound at each section (inlet, throat, exit) of the nozzle.
- Mach No. at each section (inlet, throat, exit) of the nozzle.
I don't have a real grasp of this subject, but from some text-books I've figured out the following, and mainly, I just want to ensure what I'm doing is correct.
•Mass Flow Rate
Density x Surface Area x Velocity Density = pRT, so I assume I'd take P1, and divide by (T1 x Universal Gas Constant)
Surface Area = (Pi x D12)/4
Velocity = Provided as part of the experiment.
Velocity
Continuity Equation = p1A1V1=p2A2V2 Now that I have p1 and A1 from the previous part, I should be able to rearrange to get V1? I'm assuming this would be the same for V3, V4?
Speed of Sound
I have this for a perfect gas: a = ROOT(yGcRT) So Root(specific heat ratio(?) x Newton's Constant x Gas Constant x Temperature?)
Not sure how to calculate each part of this
Mach No. M2 = V2/(specific heat ratio(?) x Newton's Constant x Gas Constant x Temperature?)
Any help at all would be appreciated, I've worked out what I can, as I don't want to flat-out ask for answers...
Thank you! :)