Purpose

The purpose of this lab is The purpose of this lab is to explore how the dimensions of a glider effect its capability to fly.

Procedure

Using the design constraints in the table below design a glider in the Aery 32 software.

Design Challenge 1

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Original Constraints

It will fly!

The stabilizer may be larger than necessary.

Dimensions & Statistics

Aery Evaluation Number: 136

Fuselage Length: 65.00 cm

Wing Location: 30.00 cm

Stabilizer Location: 57.00 cm

Vertical Tail Location: 57.00 cm

Mass at Nose: 11.15 g

Center of Gravity Location: 37.94 cm

Neutral Point Location: 39.33 cm

ESTIMATED Mass: 76.26 g

Wing Loading 0.095 g/cm^2

Throwing Velocity: 20.00 km/hr

Flight Angle of Attack: 5.25 degrees

Stabilizer Incidence Angle: -1.23 degrees (positive upward)

ESTIMATED Stall Angle: 8.41 degrees

ESTIMATED Stall Velocity: 15.07 km/hr

ESTIMATED Glide Angle: 3.57 degrees (positive downward)

ESTIMATED CDo: 0.019

Wing Span: 80.00 cm

Planform Area 800.00 cm^2

Wing Root Chord: 10.00 cm

Wing Taper Ratio: 1.00

Wing Tip Chord: 10.00 cm

Wing Tip Sweep Distance: 5.46 cm

Wing Leading Edge Sweep Angle: 7.77 degrees

Wing Aspect Ratio: 8.00

CL,alpha: 4.84 1/radian

Stabilizer Span: 40.00 cm

Planform Area 320.00 cm^2

Stabilizer Root Chord: 8.00 cm

Stabilizer Taper Ratio: 1.00

Stabilizer Tip Chord: 8.00 cm

Stabilizer Tip Sweep Distance: 2.86 cm

Stabilizer Leading Edge Sweep Angle: 8.13 degrees

Stabilizer Aspect Ratio: 5.00

CL,alpha: 4.25 1/radian

Vertical Tail Height: 20.00 cm

Planform Area 160.00 cm^2

Vertical Tail Root Chord: 8.00 cm

Vertical Tail Taper Ratio: 1.00

Vertical Tail Tip Chord: 8.00 cm

Vertical Tail Tip Sweep Distance: 0.00 cm

Vertical Tail Leading Edge Sweep Angle: 0.00 degrees

Conclusions

1.Explain which glider or aircraft term were difficult to understand and the correct definition

The Root Chord of the vertical tail was difficult to understand, the definition of the root chord is the length of the top part of the tail of the glider.

2.Explain any challenges if someone else were to construct your design using the AERY print

It is hard to figure out where the stabilizer should go to make the glider flyable.

3.Explain any challenges faced using the AERY software and how you overcame those challenges.

The first time I tried to make a glider I was getting a suggestion that was not working, that was because I put the wing and tail on the wrong sides of the glider, so I had tor restart.

Design Challenge 2

It will fly!

The stabilizer may be larger than necessary.

Dimensions & Statistics

Aery Evaluation Number: 157

Fuselage Length: 30.00 cm

Wing Location: 19.00 cm

Stabilizer Location: 1.30 cm

Vertical Tail Location: 22.00 cm

Mass at Nose: 2.00 g

Center of Gravity Location: 19.90 cm

Neutral Point Location: 20.87 cm

ESTIMATED Mass: 29.07 g

Wing Loading 0.083 g/cm^2

Throwing Velocity: 20.00 km/hr

Flight Angle of Attack: 4.21 degrees

Stabilizer Incidence Angle: 1.36 degrees (positive upward)

ESTIMATED Stall Angle: 9.55 degrees

ESTIMATED Stall Velocity: 13.57 km/hr

ESTIMATED Glide Angle: 3.76 degrees (positive downward)

ESTIMATED CDo: 0.018

Wing Span: 50.00 cm

Planform Area 350.00 cm^2

Wing Root Chord: 10.00 cm

Wing Taper Ratio: 0.40

Wing Tip Chord: 4.00 cm

Wing Tip Sweep Distance: 6.23 cm

Wing Leading Edge Sweep Angle: 14.00 degrees

Wing Aspect Ratio: 7.14

CL,alpha: 4.64 1/radian

Stabilizer Span: 20.00 cm

Planform Area 87.50 cm^2

Stabilizer Root Chord: 5.00 cm

Stabilizer Taper Ratio: 0.75

Stabilizer Tip Chord: 3.75 cm

Stabilizer Tip Sweep Distance: 5.77 cm

Stabilizer Leading Edge Sweep Angle: 30.00 degrees

Stabilizer Aspect Ratio: 4.57

CL,alpha: 3.77 1/radian

Vertical Tail Height: 19.00 cm

Planform Area 83.13 cm^2

Vertical Tail Root Chord: 5.00 cm

Vertical Tail Taper Ratio: 0.75

Vertical Tail Tip Chord: 3.75 cm

Vertical Tail Tip Sweep Distance: 10.97 cm

Vertical Tail Leading Edge Sweep Angle: 30.00 degrees

Glider Design Research Funding - Research Journal Entry

Vertical Tail Leading Edge Sweep Angle: 0.00 degrees

Glider Design Research Funding - Call for Phase I Proposals

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Underlying Principles

The underlying principles on our glider was that the larger the wing area of a glider, the more lift it can produce. For this reason we tried to make our glider's wings as large as possible.

Design Features

Our wing length is very large, this is because we want to create maximum lift. The fuselage length is at a maximum so we have more room to move around parts in order to create the glider in AERY. Objectively, longer fuselages are bad because of the weight but we felt that it was worth the trade off.

Feasibility

One practical limit of our project is that aery does know the conditions of the wind during flight. For that reason, we will have to manipulate the nose mass in order to compensate.

Conclusion

1. Funding for a new project is always limited in some way. How does the proposal process ensure that the idea being proposed will satisfy the project requirements?

For a proposal to be approved the project must match all design constraints.

2. Projects fail not due to a lack of solid designs but instead due to other issues. Describe these issues and explain how the proposal process ensures that the design with the highest likelihood of success can be selected.

The process limits the possibility of the project failing because of design flaws. You can also address other possible ways, such as building accidents or unfavorable circumstances(wind in this case) that could cause a failure and attempt to provide a safety net.

3. Describe the most persuasive elements of your proposal.

The high wind spam guarantees a significant amount of lift.

4. Explain why someone would have either a positive or negative impression after reading through your proposal for the first time.

Someone would have a positive impression because of the aforementioned reasons.

<Note: Here is where you continue your ePortfolio work after building your plane!>

Construction

We started by cutting the pieces from the wood, starting withe biggest piece. We sanded the ends of each piece and then glued it only the glider, starting with the wing the the appendage. Afterwards, we had excess time so we painted the glider after adding a nose weight.

Test Flights

Our glider got stuck on the top of the roof of the building so we could not continue to fly it

Production Flights

Flight 1: 66 feet

After flight one our glider got stuck on the top of the roof of the building so we could not continue to fly it

Final Conclusions

1. Explain the strengths and weaknesses of a competitive trial as a method to identify an optimal design.

Competition gives a simple way to compare designs, though competition may outweigh one trait over another. For example. distance was more weighted over stability and straightness of flight.

1. Explain differences between your glider’s performance through flight testing that was unexpected based on the AERY software predicted flight characteristics.

The nose mass of our glider had to be changed because the AERY nose mass was much too light.

1. Based on the entire flight test data, from every group, explain what conclusion you can make about optimal glider designs for long-distance flight.

The best glider has a massive amount of nose weight to propel it due to it's larger moment of inertia.