REPORT
Glider making
Submitted by:
TEAM 8 (BATCH 2)
Dhonish S D
Mithra Nandhana B A
Sidharth D
Pridwi Rajesh
Swathe M K
Ananthan S
1. Introduction
This report presents the design of a glider developed to achieve stable and efficient
unpowered flight. The design process involved determining suitable dimensions for the wing,
fuselage, and tail surfaces while ensuring aerodynamic stability and structural feasibility.
2. Design Configuration
3. Design Calculations
1. Wing Span = 70 𝑐𝑚
2. Chord Length = 12.5 𝑐𝑚
3. Wing Area = 𝑆𝑝𝑎𝑛 × 𝐶ℎ𝑜𝑟𝑑 𝐿𝑒𝑛𝑔𝑡ℎ
= 875 𝑐𝑚
= 875 × 2
= 1750 𝑐𝑚
(
)^
4. Aspect Ratio =
=
70
12.5
= 5.6
=
5. Fuselage Length = 52.5 𝑐𝑚
6. Tail Area = 20% 𝑜𝑓 𝑊𝑖𝑛𝑔 𝐴𝑟𝑒𝑎
= 0.2 × 1750
= 350 𝑐𝑚
7. Tail Moment Arm = 1.5 × 𝐶ℎ𝑜𝑟𝑑
= 1.5 × 12.5
= 18.75 𝑐𝑚
8. Fin (Vertical Stabilizer/ Rudder) = ½ 𝑜𝑓 𝑡𝑎𝑖𝑙𝑝𝑙𝑎𝑛𝑒 𝑎𝑟𝑒𝑎
= ½ × 350
= 175 𝑐𝑚
9. CG from Wing Leading Edge = 3.125 cm to 4.125 cm
4. Conclusion
Based on the selected dimensions and calculated aerodynamic parameters, the glider design
satisfies the basic requirements for stable flight and efficient gliding performance. The
obtained values indicate that the design is suitable for fabrication and flight testing.