Glider design
While using the AERY software, you can change everything about the glider. You can change the nose weight, the fuselage length, the location of all parts, the wing span, leading edge sweep angle, and the same for the stabilizers.
Benefits of Computer Based Models
The AERY software tells you what you need to improve. You could compute the same information by knowing that to balance the glider you need to either move the wings, or add weight to the nose or tail of the glider. Even if you don’t know how to fix the glider, the software tells you what to do.
Glider Design Prints and information
Aery Evaluation Number: 145
Fuselage Length: 30.03 cm Wing Location: 9.83 cm Stabilizer Location: 22.03 cm Vertical Tail Location: 22.03 cm Mass at Nose: 13.94 g Center of Gravity Location: 13.48 cm Neutral Point Location: 14.16 cm ESTIMATED Mass: 51.35 g Wing Loading 0.103 g/cm^2 Throwing Velocity: 20.00 km/hr Flight Angle of Attack: 6.55 degrees Stabilizer Incidence Angle: -1.21 degrees (positive upward) ESTIMATED Stall Angle: 9.59 degrees ESTIMATED Stall Velocity: 15.82 km/hr ESTIMATED Glide Angle: 4.06 degrees (positive downward) ESTIMATED CDo: 0.018 Wing Span: 50.09 cm Planform Area 500.90 cm^2 Wing Root Chord: 10.00 cm Wing Taper Ratio: 1.00 Wing Tip Chord: 10.00 cm Wing Tip Sweep Distance: 0.00 cm Wing Leading Edge Sweep Angle: 0.00 degrees Wing Aspect Ratio: 5.01 CL,alpha: 4.28 1/radian Stabilizer Span: 30.50 cm Planform Area 195.20 cm^2 Stabilizer Root Chord: 8.00 cm Stabilizer Taper Ratio: 0.60 Stabilizer Tip Chord: 4.80 cm Stabilizer Tip Sweep Distance: 4.09 cm Stabilizer Leading Edge Sweep Angle: 15.00 degrees Stabilizer Aspect Ratio: 4.77 CL,alpha: 4.11 1/radian Vertical Tail Height: 10.01 cm Planform Area 68.07 cm^2 Vertical Tail Root Chord: 8.00 cm Vertical Tail Taper Ratio: 0.70 Vertical Tail Tip Chord: 5.60 cm Vertical Tail Tip Sweep Distance: 2.68 cm Vertical Tail Leading Edge Sweep Angle: 15.00 degrees |
Aery Evaluation Number: 183
Fuselage Length: 30.03 cm Wing Location: 20.03 cm Stabilizer Location: 1.31 cm Vertical Tail Location: 22.03 cm Mass at Nose: 0.22 g Center of Gravity Location: 23.73 cm Neutral Point Location: 24.08 cm ESTIMATED Mass: 25.12 g Wing Loading 0.072 g/cm^2 Throwing Velocity: 20.02 km/hr Flight Angle of Attack: 4.43 degrees Stabilizer Incidence Angle: 2.95 degrees (positive upward) ESTIMATED Stall Angle: 21.58 degrees ESTIMATED Stall Velocity: 8.86 km/hr ESTIMATED Glide Angle: 3.62 degrees (positive downward) ESTIMATED CDo: 0.016 Wing Span: 50.09 cm Planform Area 350.63 cm^2 Wing Root Chord: 10.00 cm Wing Taper Ratio: 0.40 Wing Tip Chord: 4.00 cm Wing Tip Sweep Distance: 6.27 cm Wing Leading Edge Sweep Angle: 14.05 degrees Wing Aspect Ratio: 7.16 CL,alpha: 4.64 1/radian Stabilizer Span: 5.05 cm Planform Area 22.09 cm^2 Stabilizer Root Chord: 5.00 cm Stabilizer Taper Ratio: 0.75 Stabilizer Tip Chord: 3.75 cm Stabilizer Tip Sweep Distance: 1.46 cm Stabilizer Leading Edge Sweep Angle: 30.00 degrees Stabilizer Aspect Ratio: 1.15 CL,alpha: 1.73 1/radian Vertical Tail Height: 22.05 cm Planform Area 96.47 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: 12.73 cm Vertical Tail Leading Edge Sweep Angle: 30.00 degrees |
Dimensions & Statistics
Aery Evaluation Number: 206 Fuselage Length: 30.16 cm Wing Location: 15.74 cm Stabilizer Location: 4.37 cm Vertical Tail Location: 24.99 cm Mass at Nose: 0.00 g Center of Gravity Location: 16.94 cm Neutral Point Location: 17.33 cm ESTIMATED Mass: 5.68 g Wing Loading 0.045 g/cm^2 Throwing Velocity: 20.06 km/hr Flight Angle of Attack: 4.38 degrees Stabilizer Incidence Angle: 4.76 degrees (positive upward) ESTIMATED Stall Angle: 54.74 degrees ESTIMATED Stall Velocity: 5.64 km/hr ESTIMATED Glide Angle: 6.33 degrees (positive downward) ESTIMATED CDo: 0.018 Wing Span: 16.59 cm Planform Area 126.40 cm^2 Wing Root Chord: 7.62 cm Wing Taper Ratio: 1.00 Wing Tip Chord: 7.62 cm Wing Tip Sweep Distance: 0.00 cm Wing Leading Edge Sweep Angle: 0.00 degrees Wing Aspect Ratio: 2.18 CL,alpha: 2.86 1/radian Stabilizer Span: 2.64 cm Planform Area 15.39 cm^2 Stabilizer Root Chord: 7.62 cm Stabilizer Taper Ratio: 0.53 Stabilizer Tip Chord: 4.04 cm Stabilizer Tip Sweep Distance: 0.76 cm Stabilizer Leading Edge Sweep Angle: 30.00 degrees Stabilizer Aspect Ratio: 0.45 CL,alpha: 0.75 1/radian Vertical Tail Height: 4.52 cm Planform Area 12.40 cm^2 Vertical Tail Root Chord: 3.92 cm Vertical Tail Taper Ratio: 0.40 Vertical Tail Tip Chord: 1.57 cm Vertical Tail Tip Sweep Distance: 2.61 cm Vertical Tail Leading Edge Sweep Angle: 30.00 degrees |
Final Design IPTs
Final design IDWs
Final Design Assembly
Flight Performance Chart
Conclusion Questions
1. Was the glider as stable as you expected? Why or why not might this be so?
It wasn't stable, since the fuselage was a different size than what I anticipated.
2. What techniques did you use to “trim” the glider for straight and gently descending flight?
I had to add weight to the front, the back, and the left wing, in order for the glider to fly.
3. How many test flights were required to get the glider trimmed for long distance, straight-line flight? Was this expected? Why or why not?
It required about 5 tests, and I expected it to happen as soon as I saw the fuselage size was different than the one I was planning to use.
It wasn't stable, since the fuselage was a different size than what I anticipated.
2. What techniques did you use to “trim” the glider for straight and gently descending flight?
I had to add weight to the front, the back, and the left wing, in order for the glider to fly.
3. How many test flights were required to get the glider trimmed for long distance, straight-line flight? Was this expected? Why or why not?
It required about 5 tests, and I expected it to happen as soon as I saw the fuselage size was different than the one I was planning to use.