1. An airfoil is the shape of a wing or blade that produces lift as air flows around it. It is inspired by the shape of a fish. 2. The key parts of an airfoil are the leading edge, which meets the air first, and the trailing edge, which smooths air flow. 3. NACA airfoils use a numbering system to describe characteristics like camber, thickness, and optimal lift coefficients. The 4-digit system describes camber, location of maximum camber, and thickness, while the 5-digit system provides more details.

1. Assignment
Lahore School of Aviation
The University of Lahore
TOPIC: Airfoils
 Program: BS Aviation Management Semester: 01
 Course: Principles of Flights Date:1-Jan-2017
 Instructor: Imtiaz Hussain Batch: 06
 Term: FALL 2016 Section: A

2. Presented By
 H M Noshairwan (BAM02163111)

3.  INTRODUCTION
 DEFINITION
 PARTS
 TYPES
 NACA 4 DIGITS
 NACA 5 DIGITS
AIRFOILS

4. Introduction
Airfoil is a basic part of an aircraft. It is used in many parts of an aircraft as it is
basically a shape which is used to produce the lift.
 Here comes the question that what actually is an airfoil?
So let us discuss the airfoils in detail.

5. Airfoil:
“ it is actually the shape of the wing or blade which is used in propeller,
wings, fuselage, vertical and horizontal stabilizer in order to produce the
lift.

6. Shape:
 It’s shape is just like the shape of the fish as it was made by getting the
inspiration of a fish swimming against the heavy flow of water.

7. Parts:
There parts of airfoil are as follows.
 Leading edge
 Trailing edge

8. Leading edge:
The frontal smooth part of the airfoil is know as the leading edge.
 This part of the air foil meets the air first.
 It is designed according to the functioning of the airplane as if the
airplane is required to achieve more speed then it would be sharp

9. Trailing edge:
 It is the terminating part of the airfoil.
 It is designed to smoothen the flow of air at the end so that we can avoid
the turbulence of air flow.

10. Basic terminologies of an airfoil:
 Chord: The imaginary straight line joining the leading and trailing edge.
 MAC : It is referred as the mean aerodynamic camber. It divides the airfoil in
two equal parts.
 Camber: It is the maximum vertical distance between chord and MAC.

11. Types:
 There are two types of an airfoil.
 Symmetric or non cambered airfoil: The airfoil in which MAC and chord lies
on one another. It is symmetric between the top and bottom surface of an airfoil It means
that it doesn’t have a camber.
Asymmetric or cambered airfoil: It is the airfoil in which the chord line doesn’t
divide the airfoil in two equal parts. So camber does exist in it.
The cambered airfoil produces more lift while the non
cambered provide more speed.

12. NACA AIRFOIL
Numbering system
 Naca Stand for National Advisory Committee for Aeronautics.
 We will study two types of Naca digital airfoils.
o Naca 4 digit
o Naca 5 digit

13. Naca 4 digits:
 We use this system to interpret the information regarding the airfoil.
 In NACA 4 digits
First digit express the camber in percent chord.
Second digit gives the location of the maximum camber located in tenth
of chord
And the last two digits gives the thickness in percent chord

14. NACA 4 Digits
 Example: NACA 4526
 Thus 4526 has a maximum camber of 4% of chord located at 50% chord
back from the leading edge and is 26% thick.

15. Naca 5-digits airfoil
 In NACA 5-digits.
 The first digit, when multiplied by 0.15, gives the designed theoretical
optimum lift coefficient at the ideal angle-of-attack.
 The second digit, when multiplied by 5, gives the relative position, as a
percentage, of the point of maximum camber along the chord from the
leading edge.
 The third digit indicates whether the camber is simple (0) or reflex (1).
 The fourth and fifth digits give the maximum thickness of the airfoil (as
a percentage of the chord), the same as 4-digit NACA profiles.