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Rocket Nozzle Design

Group Members:
Mike
Nick
Introduction...

Presentation Outline


Introduction (Nick)



Brief Theory / FLUENT Modeling (Mike)



Literature / Experimental Data (Nick)



Conclusion (Mike)
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.
Introduction...

Which simplifications?
The Nozzle Configurations we modeled:
1)
2)
3)
4)

Orifice
Converging Nozzle
Diverging Nozzle
Converging-Diverging

(Click on links above to see the various
configurations)
Introduction...

Rocket Particulars
The type of rocket we modeled:
1) Solid Propellant / Core Burning
Core burning rockets burn propellant from the
“inside out.”
This is in comparison to endburning rockets which burn
propellant from the “bottom up.”
Graphic from: http://www.sewanee.edu/physics/SEMINARS/HTML%20Rowland/sld011.htm
Introduction...

Rocket Particulars
The size of rocket
we modeled:
0.25 Inch diameter
casing
2) 2.25 Inches Long
Brief Theory

How to calculate thrust
The general thrust
equation is given as
follows:

Graphic from: http://members.aol.com/ricnakk/th_thrst.html
GAMBIT
Boundary
Conditions
GAMBIT

The Mesh
Triangular Elements
40 to 400
Intervals/Inch
FLUENT

Assumptions
1)
2)
3)
4)

Axisymmetric 2D Flow
Steady State / Constant Pressure Inlet
Compressible Flow
Ideal Gas (air)
FLUENT

Particular Settings
1)

2)
3)
4)

On all configurations the iterations
were run to a residual of 1e-3
Turbulent Flow (K-E model)
Variable Density
Used 2nd Order Equations to Calculate
Density / Pressure / Momentum
FLUENT

Velocity Contour Plots
FLUENT

Pressure Contour Plots
FLUENT

Density Contour Plots
FLUENT

Results
Nozzle Type

Force (oz)

Converging

4.56841

Diverging

3.81035

Regular Orifice

4.18331

Converging - Diverging

7.53282
FLUENT

Graphical Results
FLUENT Results

Thrust (oz)

8.00

Converging

7.00
6.00

Diverging

5.00
4.00
3.00

Regular Orifice

2.00
1.00
0.00
1

Converging
Diverging
Literature
The preponderance of literature clearly shows
the Converging – Diverging Nozzle as the most
efficient nozzle design.

Diagrams like this
(right) are not
uncommon:

Graphic from: http://www.nakka-rocketry.net/lambda_p.html
Literature
Similar Pressure Trends
Experimental Data

Introduction

Homemade rockets with these four
various nozzle geometries were built
and tested. All thrust values were
measured and recorded.
Experimental Data

Experimental 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.
Experimental Data

Testing Using Method #1
For record keeping, a
camcorder was
zoomed up close to the
scale and recording.

Note the metal plate protecting the
plastic of the scale.
Experimental Data

Method #1 (Thrust Downward)
Set 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

Nozzle Type
Experimental Data

Experimental Setup Method #2
Method #2
In this case the
nozzle was
placed into a
hollow tube and
thrust was
directed
upward. Thus
the rocket
pushed onto
the scale.
Experimental Data

Testing Using Method #2
Note the
camcorder was
zoomed up
close to the
scale.
(Right) Movie of
ConvergingDiverging Run:
Click on Image
to Play
Experimental Data

Data Using Method #2
We were able to
go back and
watch our results
on TV in slow
motion.
Experimental Data

Method #2 (Thrust Upwards)
Nozzle Type

Set 3 (oz)

Converging

0.6

Diverging

0.45

Regular Orifice

0.25

Converging - Diverging

0.90
Conclusion

FLUENT Results

Thrust (oz)

8.00

Converging

7.00
6.00

Diverging

5.00
4.00
3.00

Regular Orifice

2.00
1.00
0.00
1

Converging
Diverging

Experimental Data Results

Thrust (oz)

1

Converging

0.8

Diverging

0.6
0.4

Regular Orifice

0.2
0
1

Converging
Diverging
Next time…
Questions?
Converging/
Diverging
Diverging
Converging
Orifice

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