This document summarizes the design of a remote controlled aircraft. It discusses selecting a symmetrical airfoil with a NACA0012 profile for its low speed stability. It describes control surfaces like ailerons and elevators. Calculations are shown for wing area based on lift and drag coefficients. A CATIA model and flow simulation were also created. The design focuses on stability concepts like neutral point, center of pressure, and aerodynamic center. References include aerodynamics textbooks and software used like JAVA, Flow Design, and CATIA V5.

1. Roopal Raj
Sandeep Kr. Mishra
Shreya Srivastava
6th B

2. Introduction:
 A RC aircraft has all the dynamic characteristics which
are present in actual aircraft.
 RC Aircrafts can be used to carry
some mass of small value or also
use by defense authority by applying
a spy camera on it.
 RC aircraft are also used by research
and development department in order to check the
feasibility of any design.

3. Airfoil:
 An airfoil is the 2D cross-section shape of the wing,
which creates sufficient lift with minimal drag.
 Types:
 Flat bottom airfoil
 Semi-Symmetric airfoil
 Symmetrical airfoil

4. Terminology

5. Airfoil selection:
 We opted Symmetrical
airfoil because It is use
for airplanes having
low Mach no. and
good stability.
 The selected profile
was “naca0012” .

6. Lift
• The component of the total aerodynamic force of an airfoil that is
perpendicular to the relative wind.
Drag
• The component of the total aero –
dynamic force of an airfoil that is
parallel to the relative wind.
FL = CL ρ A
v²/2
FD = CD ρ A
v²/2

7. Motion Characteristics

8. Control Surfaces :
Ailerons:
 An aileron is a hinged flight control
surface usually attached to the trailing
arm of each wing of a fixed-wing
aircraft.
 Movement around this axis is called
'rolling' or 'banking'.

9. Rudder:
 The rudder are hinged on rear
surface, making as a vertical stabilizer.
and its area is half of the whole vertical
stabilizer.
Elevators:
 The elevators are hinged on rear
surface, making as a whole a tail
plane or horizontal stabilizer.

10. Stability Concept:
 Stability may be defined as follows:
- Positive stability: tends to return to original condition
after a disturbance.
- Negative stability: tends to increase the disturbance.
- Neutral stability: remains at the new condition.
 Dynamic instability may be prevented by an even
distribution of weight inside the fuselage, avoiding too
much weight concentration at the extremities or at the CG.

11. Neutral point:
 Neutral Point (NP) is the Aerodynamic Centre of the whole
aircraft.
Centre of pressure:
 Centre of pressure Cp is a point on the wing where the net
lift force assume to be act.
 The distance of the Cp from leading edge is at distance of
“c/4” unit where “c ” is the chord length.
Aerodynamic center(AC):
 It is a point on the wing where the net pitching moment is
always constant.

12. Stability configuration:

13. Wing Analysis on JAVA Applet:

14. Calculations:
 Wing area = FL ×2 /CL ×ρ ×V²
= 10 ×2/0.278 ×1.228 ×10²
= 0.188m²
 Wing dimensions by taking aspect ratio as 6 = 0.188/1.06
= 0.178m
 Area of horizontal stabilizer = wing area/4
= 0.188/4
= 0.94m²
 Area of vertical stabilizer = Area of horizontal stab./2
= 0.94/2

15. = 0.47m²
From given diagram:
L = 0.50 × 0.94/(0.188+ 0.94)
= 0.42m.
FD = 0.0764 × 0.188 ×10 ×1.228/2
= 0.861 N

16. CATIA Model :

17. Flow simulation:

19.  John J. Bertin “Aerodynamics for Engineers”
Fourth Edition U.S Air force Academy.
 John D. Anderson “Introduction to flight
Dynamics” Third edition.
 Wikipedia
 Softwares used :
- JAVA Applet
- Flow design
- CATIA V5
Reference: