rocketproject
DESCRIPTION
TRANSCRIPT
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Rocket Nozzle DesignRocket Nozzle Design
Group Members:Group Members:MikeMikeNickNick
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Introduction...
Presentation Outline Introduction (Nick)
Brief Theory / FLUENT Modeling (Mike)
Literature / Experimental Data (Nick)
Conclusion (Mike)
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Introduction...
Project Objectives
1)To analyze four simplified nozzle geometries in a model rocket and calculate their maximum thrust.
2) Compare the theoretical and experimental thrust of these nozzles. Choose the best nozzle based on our data.
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Introduction...
Which simplifications?The Nozzle Configurations we modeled:1) Orifice 2) Converging Nozzle3) Diverging Nozzle4) Converging-Diverging
(Click on links above to see the various configurations)
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Introduction...
Rocket Particulars
The type of rocket we modeled:
1) Solid Propellant / Core Burning
Core burning rockets burn propellant from the “inside out.”
Graphic from: http://www.sewanee.edu/physics/SEMINARS/HTML%20Rowland/sld011.htm
This is in comparison to end-burning rockets which burn propellant from the “bottom up.”
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Introduction...
Rocket ParticularsThe size of rocket
we modeled:
0.25 Inch diameter casing
2) 2.25 Inches Long
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Brief Theory
How to calculate thrust
The general thrust equation is given as follows:
Graphic from: http://members.aol.com/ricnakk/th_thrst.html
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GAMBIT
BoundaryConditions
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GAMBIT
The Mesh
Triangular Elements
40 to 400 Intervals/Inch
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FLUENT
Assumptions
1) Axisymmetric 2D Flow2) Steady State / Constant Pressure Inlet3) Compressible Flow 4) Ideal Gas (air)
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FLUENT
Particular Settings1) On all configurations the iterations
were run to a residual of 1e-32) Turbulent Flow (K-E model) 3) Variable Density4) Used 2nd Order Equations to Calculate
Density / Pressure / Momentum
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FLUENT
Velocity Contour Plots
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FLUENT
Pressure Contour Plots
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FLUENT
Density Contour Plots
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FLUENT
Results
Nozzle Type Force (oz)
Converging 4.56841
Diverging 3.81035
Regular Orifice 4.18331
Converging - Diverging 7.53282
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FLUENT
Graphical Results
FLUENT Results
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1
Th
rus
t (o
z)
Converging
Diverging
Regular Orifice
ConvergingDiverging
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Literature
Graphic from: http://www.nakka-rocketry.net/lambda_p.html
The preponderance of literature clearly shows the Converging – Diverging Nozzle as the most efficient nozzle design.
Diagrams like this (right) are not uncommon:
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LiteratureSimilar Pressure Trends
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Experimental DataIntroduction
Homemade rockets with these four various nozzle geometries were built and tested. All thrust values were measured and recorded.
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Experimental DataExperimental Setup Method #1
Method #1
In this case the nozzle thrust was downward onto the scale.
Before ignition, a thin metal plate was placed on top of the scale to protect it from the flame.
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Experimental DataTesting Using Method #1
Note the metal plate protecting the plastic of the scale.
For record keeping, a camcorder was zoomed up close to the scale and recording.
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Experimental DataMethod #1 (Thrust Downward)
Nozzle TypeSet 1
(oz)Set 2
(oz)
Converging 0.5 0.4
Diverging 0.25 dud
Regular Orifice 0.6 0.7
Converging - Diverging n/a n/a
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Experimental DataExperimental Setup Method #2Method #2
In this case the nozzle was placed into a hollow tube and thrust was directed upward. Thus the rocket pushed onto the scale.
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Experimental DataTesting Using Method #2
Note the camcorder was zoomed up close to the scale.(Right) Movie ofConverging-Diverging Run:Click on Image to Play
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Experimental DataData Using Method #2
We were able to go back and watch our results on TV in slow motion.
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Experimental DataMethod #2 (Thrust Upwards)
Nozzle Type Set 3 (oz)
Converging 0.6
Diverging 0.45
Regular Orifice 0.25
Converging - Diverging 0.90
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Conclusion FLUENT Results
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1T
hru
st
(oz)
Converging
Diverging
Regular Orifice
ConvergingDiverging
Experimental Data Results
0
0.2
0.4
0.6
0.8
1
1
Th
rus
t (o
z)
Converging
Diverging
Regular Orifice
ConvergingDiverging
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Next time…
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Questions?
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Converging/Diverging
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Diverging
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Converging
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Orifice