1. FOXTROT
1. S Darshan: BMS College Of Engineering
2. Syed Mohommed Shoaib: Gogte Institute Of Technology
3. Akash Revankar: Gogte Institute Of Technology
4. Mangesh Urankar: KLE Society’s Dr. M.S. Sheshgiri
College Of Engineering and Technology
2. 1. Aircraft Parameters
2. Fuselage Design
3. Wing Design
4. Stability
5. Calculations
6. Uniqueness
7. Control
8. Construction
9. Acknowledgements and References
10. Conclusion
TABLE OF CONTENTS
4. Aircraft Parameters
Wing Span= 49.39”
Leading Edge Sweep= 100
Taper Ratio=0.64
Aspect Ratio= 8.865
Area= 275.156 sq.inches
MAC Position= 2.76 from LE
5. Fuselage Design
• Chines were used in our design
Generate powerful vortices which provide additional lift near the front
of the aircraft
Angle of incidence of tapered wings could be reduced allowing for
greater stability
Makes it harder for the wings to stall
• A nozzle at the bottom the aircraft which
would serve the dual purpose of providing
Stability
Decrease the velocity of the air before it reaches the end of the
fuselage.
6. Wing Design
• Chosen MH78 Airfoil Characteristics
Designed for Flying wings
Smooth Stall Characteristics
Positive Pitching Moment
Relatively High Clmax
• Turbulators
• Sweep
• Taper Ratio
• Winglets serve a dual purpose
Reduce Wing Tip Vortices
Provide Directional Stability
7. Stability
• LONGITUDNAL STABILITY
SM= (Location of aero center-location of CG)/MAC
XFLR5 was used to calculate the AC location on the
planform, in order to determine where the CG should
be placed for positive SM.
This being a theoretical value, we decided the minor
changes can be done by re-positioning the batteries.
• DIRECTIONAL STABILITY
As a rear vertical stabilizer was not allowed directional
stability was an issue.
We used 2 features to provide directional stability in
the glider
Winglets
Nozzle
8. CALCULATION
• Aspect Ratio= Tip Chord/ Root Chord
= 7.0866/11.023
= 8.865
• Lift due to Wings = Fw = 0.5*rho*Cl*V^2*A
= 0.5*1*1.4*(5*5)*0.17752
= 3.1 N
• Ain*Vin=Aout*Vout
Vout= 3750*5/6000
= 2.34375 m/s
• Stability: -Fw(27.5)-Fn(325.8)+ Ft(401.126)=0
-(3.1*27.5)-(0.3*325.8) + (Ft * 401.126)=0
Ft= 0.45 N
• Lift due to Tail=0.5*rho*Cl*<V>2^ + rho* V*C*L
0.45= 0.5*0.9*(3.67*3.67) + 5*1.33*L
L= 0.09m=9 cms
9. UNIQUENESS
• To provide directional stability without using a
rudder, a nozzle at the belly of the aircraft was
used.
• The fuselage of most aircrafts do not
contribute to lift. The inclusion of chines
makes the fuselage unique.
• Achieving pitch, yaw and roll using a single
composite control surface on each wing and
only 2 servos.
11. CONSTRUCTION
The materials that were used for the
construction of the glider were:
Balsa Wood- for the frame skeleton
Styrofoam- for the entire body of the glider
Carbon Fiber- used to reinforce the wings
12. ACKNOWLEDGEMENTS AND REFERENCES
• Thank Our Respective college staff for their co-operation
• Thank Shaastra for providing us with the opportunity to
participate
• Catia V5 Reference Guide by Sham Tiko
• Mechanics Of Flight by A.C. Kermode
• Model Aircraft Aerodynamics by Martin Simons
13. CONCLUSION
• Designing and building a flying wing provided
unique challenges which enhanced the teams
understanding of aircraft design
• The Competition restrictions made us use out
of the box designs to achieve.
