TECHNICAL REPORT NO. 7: FUSELAGE
DESIGN
GROUP 2: SPECTRON 320
INSTRUCTOR:
ENGR. BRYAN D. LUSTRE
DATE: 03/09/2025
RATING:
PAGE NO.: 1 OF 5
ISSUE NO.: 1
AE 416 - AIRCRAFT DESIGN
TECHNICAL REPORT NO. 7
FUSELAGE DESIGN
ADAM ANDA
DANIEL JOSEPH BALTAR
MICHAEL ANGELO CASTRO
JUSTIN MARON DELA CRUZ
PATRICK DORIA
RUSSELL LASTRA
ADRIAN NARVACAN
STEPHENE ROSS PULIDO
SUBMITTED TO:
ENGR. BRYAN D. LUSTRE
TECHNICAL REPORT NO. 7: FUSELAGE
DESIGN
GROUP 2: SPECTRON 320
INSTRUCTOR:
ENGR. BRYAN D. LUSTRE
DATE: 03/09/2025
RATING:
PAGE NO.: 2 OF 5
ISSUE NO.: 1
Reference 1: Aircraft Design: A Conceptual Approach by Daniel P. Raymer
Figure 1: Statistical equations for fuselage length estimation for aircraft
1.1 Fuselage Length
FL = a(Wo)c
Where:
FL = fuselage length
Wo = gross weight = 15.91726934 lbs (from Technical Report
4)
α & c = constants
By categorizing under Homebuilt-composite, the fuselage estimation
formula uses a = 3.50 and c = 0.23. Wo = 16 lbs
FL = 3.50(16)0.23 = 6.622403527
FL = 6.622403527 ft
1.2 Fineness Ratio
Estimation for subsonic drag minimization: FR = 3.0
FR =
FL
FD
TECHNICAL REPORT NO. 7: FUSELAGE
DESIGN
GROUP 2: SPECTRON 320
INSTRUCTOR:
ENGR. BRYAN D. LUSTRE
DATE: 03/09/2025
RATING:
PAGE NO.: 3 OF 5
ISSUE NO.: 1
Where:
FL = fuselage length
FD = fuselage diameter
FD =
FL
FR
=
6.62240352
3
= 2.207467842
FD = 2.207467842 ft
Reference 2. Estimation of component design weights in conceptual design phase for
tactical UAVs by Abdulhakim Essari
2.1 Fuselage Length
FL = 0.538b + 1.66
Where:
b = 7.85 ft
FL = 0.538(7.85ft) + 1.66 = 5.8233
FL = 5.8233 ft
Reference 3. Design and Fabrication of Fixed Wing UAV for Air and Underwater
Environments by Rajath Shetty, Pavan Kalyhan V, Madhu Pujar, Peddi Reddy,
Omkaram Reddy
3.1 Fuselage Length
FL = 0.70b
FL = 0.70(7.85ft)
FL = 5.495 ft
Reference 4. Design of an unmanned aircraft system for high-altitude 1 kW fuel cell
power system by William A. Reid & Ibrahim M. Albayati
4.1 Fuselage Length
FL
= 0.75
b
FL = 0.75(7.85)
FL = 5.8875 ft
TECHNICAL REPORT NO. 7: FUSELAGE
DESIGN
GROUP 2: SPECTRON 320
INSTRUCTOR:
ENGR. BRYAN D. LUSTRE
DATE: 03/09/2025
RATING:
PAGE NO.: 4 OF 5
ISSUE NO.: 1
4.2 Fineness Ratio
For subsonic aircraft: FR = 6.0 to 8.0
𝐷𝑎𝑣𝑒 =
𝐷𝑎𝑣𝑒 =
𝐷𝑎𝑣𝑒 =
Reference
1
2
3
4
Reference
1
4
4
𝐹𝐿
𝐹𝑅
5.8875
= 0.98125
6
5.8875 𝑓𝑡
= 0.735937
8
Parameters Taken
into Account
Wo
b
b
b
Fuselage Length
Parameters Taken
into Account
FL, FR
FL, FR
FL, FR
Fuselage Length
6.622403527
5.8233
5.495
5.8875
2.207467842
0.98125
0.735937
The fuselage selected for evaluation of other factors, including attachment sizes, was the one
with the smallest diameter (Ref 4B) and length (Ref 3). By doing this, the quantity of materials
that must be used and, thus, the cost, will be reduced. Reference 1 was not taken into account
for the fuselage length because it differs from the other three estimates.
TECHNICAL REPORT NO. 7: FUSELAGE
DESIGN
GROUP 2: SPECTRON 320
INSTRUCTOR:
ENGR. BRYAN D. LUSTRE
DATE: 03/09/2025
RATING:
PAGE NO.: 5 OF 5
ISSUE NO.: 1
REFERENCES
ESTIMATION OF EMPENNAGE DESIGN WEIGHT IN CONCEPTUAL DESIGN PHASE FOR
TACTICAL UAVs. (n.d.). ResearchGate. Retrieved September 24, 2024, from
https://www.researchgate.net/publication/329636650_ESTIMATION_OF_EMPENNAGE_
DESIGN_WEIGHT_IN_CONCEPTUAL_DESIGN_PHASE_FOR_TACTICAL_UAVs/fulltext/
5de2c5c3a6fdcc2837faa681/ESTIMATION-OF-EMPENNAGE-DESIGN-WEIGHT-INCONCEPTUAL-DESIGN-PHASE-FOR-TACTICAL-UAVs.pdf
Fuselage Weight Estimation in Conceptual Design Phase for Tactical Unmanned Aerial
Vehicles. (n.d.). Vision for Scientific Research and Publishing. Retrieved September 24,
2024, from
https://vsrp.co.uk/wp-content/uploads/13-IJSR-Vol.-2-No.-12-Dec-2023-Paper12-Dr.Hakim-2.pdf
Raymer, D. P. (n.d.). Aircraft Design - A Conceptual Approach - Daniel P.Raymer.
Airloads.net.
Retrieved
September
24,
2024,
from
https://www.airloads.net/Downloads/Textbooks/Aircraft%20Design-A%20Conceptual%20
Approach.pdf
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