1. Congratulations…Welcome to UTHM PARIT RAJA….A Place To Be..
DR. ZAMRI BIN OMAR Department of Aeronautical Engineering Faculty of Mechanical & Manufacturing Eng. Phone : /7711 Room: C & A4, 2nd Floor

2.  Here what STOL airplane can do !
~ 2009 STOLcompetition
~ Land & TO on a hill

3. ~(4) Configuration Layout – Geometric Sizing
Needs intuition, experience, art. Several primary considerations;
1. Overall config. ; 1 or 2 engines ? Pusher or tractor ?
2. Wing Configuration
3. Fuselage Configuration
4. CoG Location
5. Tail Sizing
6. Propeller Sizing
7. Landing Gear & Wing Placement

4. 1. Overall config ; 1 or 2 engines ?
 How do we choose ?

5. 1. Overall config ; 1 or 2 engines ?
We needs hp engine.
Available;
 Lycoming TIO-540V rated 360hp
supercharged at ft

6. 1. Overall config ; 1 engine. Pusher/tractor ?
Good airflow over wing/fuselage
Cabin noise reduced
Pilot view improved
Heavy load at the back, move CG moves backward, longitudinal stability reduced.
Prop may damage on landing
Engine cooling problem
Tractor
Heavy load in front, CG moves forward, smaller tail
Prop airflow undisturbed
Good engine cooling
Prop slipstream disturbs airflow over FL/wing root.
Skin friction drag over fuselage increased.
SELECTED tractor

7. 2. Wing configuration ? The shape : Aspect ratio : AR=b2/S Wing sweep
Taper ratio
variation of airfoil shape & thickness along span
geometric twist

8. 2. Wing configuration ?
The shape :
Aspect ratio : AR=b2/S 

9. 2. Wing configuration : The Shape : Sweep angle ??

10. 2. Wing configuration : Why forward sweep ?

11. 2. Wing configuration : Taper ratio ?
The shape :Taper ratio, =Ct/Cr
Small taper ratio  lighter wing structure

12. 2. Wing configuration : Taper ratio ?
The shape :Taper ratio, =Ct/Cr
Low taper ratio  causes undesirable flow
separation & stall behavior.

13. 2. Wing configuration : Taper ratio ?
The shape :Taper ratio, =Ct/Cr
Low taper ratio  causes undesirable flow
separation & stall behaviour.

14. 2. Wing configuration : Taper ratio ?
The shape :
Airfoil changes along the span.
geometric twist is not required.

15. 2. Wing configuration : Position ?
Low wing
Mid wing
High wing

16. 2. Wing configuration : Wing position ?
Low wing
Good for landing gear placement in the wing box
Need substantial dihedral
Due to engine location, need longer landing gear for ground clearance
Requires dihedral for lateral stability
Mid wing
Provides lowest drag
Only needs very little dihedral
Structural disadvantages bending moment support ?
Need heavy ring frames !
High wing
Allow lower fuselage, good for transport aircraft (load & unload)
More stable laterally (rolling), undesirable
Anhedral is needed to decrease roll stability
SELECTED Low wing
fillet is used to minimize undesirable drag (wing-fuselage interference)

17. 2. Wing configuration : why canards ?

18. 2. Wing configuration : why winglets ?

19. 3.Fuselage configuration :
FL must be big enough to place the engine, pilot, baggage & passenger.
where to store the fuel ? FL or wings ? - in the wings (less cg movement).
enough space in the wings to store fuel ?

20. 3.Fuel Tank Location

21. 3.Fuselage configuration :
passenger & baggage

22. 4. Center of Gravity Location :
Major weight components : already known (pilot, baggage, passenger).
can do initial estimation.

23. 4. Center of Gravity Location :
Major weight components : already known (pilot, baggage, passenger).
can do initial estimation.
area shown includes covered/projected area into the fuselage.

24. 5. Tail Sizing HT for longitudinal stability (elevator).
VT is for directional stability (rudder).
Tail size must adequate to provide sufficient control & stability.
Examine various tail configuration

25. 5. Tail Sizing
Needs some calculations !

26. 5. Tail Sizing
Needs some
calculations !

27. 6. Propeller Size prop diameter ? need calculations !
 3-blade with 6.53 ft diameter

28. 7. Landing gear & wing placement
Needs examine various LG configurations.

29. 7. Landing gear & wing placement
 Selected : tricycle

30. 7. Landing gear & wing placement
Needs some calculations !

31. 7. Landing gear & wing placement
Needs some calculations !

32.  THE RESULTING LAYOUT