Zaid Aviation Academy

Breaking the Sound Barrier:
When speed outruns sound — the air fights back.
💥 Learn how a sonic boom works.
💭 Why Mach, not knots? Let’s talk!
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Breaking the Sound Barrier: | ZAID AHSAN Breaking the Sound Barrier: When speed outruns sound — the air fights back. 💥 Learn how a sonic boom works. 💭 Why Mach, not knots? Let’s talk!

✈️🎓 CPL & ATPL Online Classes by Capt. Zaid Ahsan
🌍 DGCA (India) | EASA | CAAP (Philippines) | ICAO Standards

🧭 17+ Years Ground Instruction | 3900+ Flying Hours | 3500+ Instructional Hours
Train with Capt. Zaid Ahsan – an accomplished pilot and aviation educator with a rare blend of extensive flying experience and strong academic depth.

🎓 Unique Academic Edge:
✔️ 3 Postgraduate Degrees (HR, Biotech, Business Laws)
✔️ B.Sc. (Bioscience) with Physics , Chemistry and Mathematics
✔️ C1 French (Superior Diploma)
✔️ Dual CPL (DGCA India and CAAP, Philippines)
✔️ ICAO English Level 6

📚 Course Highlights:
✅ Full CPL & ATPL Theory – DGCA, EASA and other Civil Aviation Authority .
✅ Interactive Online Classes
✅ Regular Tests & Personalized Feedback

📲 Start your aviation journey today – Join from anywhere!
📧 [email protected]
📞 | +91 8800240895/+63 9770669426 (Both on WhatsApp)
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Zaid Aviation Academy Ground Instructor with 17+ years’ experience with total flight hours 3900 & 3500+ instructional hours. Online CPL/ATPL classes for DGCA India, EASA & other Civil Aviation Authorities Exams. Focused on real understanding, not just passing exams.

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From Cockpit to Classroom: Lessons from Aviation About Great Instruction In aviation, every take-off and landing is backed by rigorous training, structured supervision, and functional leadership. As Chief Ground Instructor and Flight Instructor at Royhle Aviation Academy, Philippines, recently delivered a session titled “Transforming Instruction: Elevating Supervision ...

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Implications of Glass Cockpit in General Aviation using Technically Advanced Aircrafts (TAA) Cockpit of Technically Advanced Cockpit General Aviation is defined as the operation of civil aircraft for the purpose other than commercial transport operations, including personal, business and instructional flying. Other examples of General Aviation flight operations are crop dusting, medical fli

Hello Everyone. If any one preparing for DGCA, India, CPL or ATPL exam, feel free to post your problems here. We will be more than happy to help you with the solution. Happy landings and safe skies 🙂

Day 3
Basic Aerodynamic Theory
Principle of Continuity: It states “The air mass flow, or mass per unit time, through the tube will be product of the cross-sectional area (A), the airflow velocity (V) and the air density (rho). Mass flow will remain a constant value at all points along the tube.
Area X Velocity X Density = Constant
Note: Because air is compressible fluid, and pressure changes in the flow will affect the air density. However at low subsonic speed

Day 2
Aerofoil

Aerofoil Terminology:
1. Aerofoil: A shape capable of producing lift with relatively high efficiency.
2. Chord Line: A straight line joining the centers of curvature of the leading and trailing edges of an aerofoil.
3. Chord: The distance between the leading and trailing edges measured along chord line.
4. Angle of Incidence: The angle between the chord line and the horizontal datum (longitudinal axis ) of the a/c. This angle is fixed for the wing, but may be variable for the tailplane.
5. Mean line or Mean camber line: A line joining the leading and trailing edges of an aerofoil equidistant from the upper and the lower surfaces.
6. Camber: Camber is curvature of aerofoil.
7. Maximum camber: The maximum distance of the mean line from the chord line. Maximum camber is expressed as a percentage of the chord, with its location as a percentage of the chord aft the leading edge. When the camber line lies above the chord line the aerofoil is said to have positive camber, and if the camber line is below the chord line it is said to have negative camber. A symmetrical aerofoil has no camber because the chord line and the camber line are co-incident.
8. Thickness: the thickness of an aerofoil is the distance between its upper and lower surfaces. The thickeness also varies from leading edge to trailing edge. An aerofoil is specified by thickness ratio or thickness chord ratio.
9. Thickness ratio or Thickness-chord ratio: The maximum thickness or depth of an aerofoil section expressed as the percentage of the chord, with its location as a percentage of the chord aft of the leading edge. The thickness and thickness distribution of the aerofoil section have a great influence on its airflow characterstic.

10. Leading Edge Radius: The radius of curvature of the leading edge. The size of the leading edge radius can significantly effect the initial airflow characteristic of the aerofoil section
11. Relative Airflow: If the wind has these three qualities then it is called to be relative airflow.
a. Direction: air parallel to and in opposite direction to the flight path of the a/c .
b. Condition: air close to but unaffected by presence of a/c, its temperature , velocity, and pressure not affected by the passage of a/c.
c. Magnitude: the magnitude of the Relative Air Flow is the TAS.
12. Effective Air Flow: if air does not possess all three of these qualities mentioned above it is referred as Effective Airflow.
13. Total Reaction: The resultant of all aerodynamic forces acting on the aerofoil section.
14. Centre of Pressure: The point on the chord line , through which lift is considered to be acting.
15. Lift: The aerodynamic force which acts at 90* to the Relative Air Flow.
16. Drag: The aerodynamic force which acts parallel to and in same direction of as of Relative Air Flow but in opposite direction of flight path.
17. Angle of attack/Aerodynamic Incidence: The angle between the chord line and Relative Airflow.
18. Effective angle of Attack: The angle between the chord line and the effective airflow is referred as the Effective Angle of Attack.

Aerofoil

Aerofoil Terminology:
1. Aerofoil: A shape capable of producing lift with relatively high efficiency.
2. Chord Line: A straight line joining the centers of curvature of the leading and trailing edges of an aerofoil.
3. Chord: The distance between the leading and trailing edges measured along chord line.
4. Angle of Incidence: The angle between the chord line and the horizontal datum (longitudinal axis ) of the a/c. This angle is fixed for the wing, but may be variable for the tailplane.
5. Mean line or Mean camber line: A line joining the leading and trailing edges of an aerofoil equidistant from the upper and the lower surfaces.
6. Camber: Camber is curvature of aerofoil.
7. Maximum camber: The maximum distance of the mean line from the chord line. Maximum camber is expressed as a percentage of the chord, with its location as a percentage of the chord aft the leading edge. When the camber line lies above the chord line the aerofoil is said to have positive camber, and if the camber line is below the chord line it is said to have negative camber. A symmetrical aerofoil has no camber because the chord line and the camber line are co-incident.
8. Thickness: the thickness of an aerofoil is the distance between its upper and lower surfaces. The thickeness also varies from leading edge to trailing edge. An aerofoil is specified by thickness ratio or thickness chord ratio.
9. Thickness ratio or Thickness-chord ratio: The maximum thickness or depth of an aerofoil section expressed as the percentage of the chord, with its location as a percentage of the chord aft of the leading edge. The thickness and thickness distribution of the aerofoil section have a great influence on its airflow characterstic.
10. Leading Edge Radius: The radius of curvature of the leading edge. The size of the leading edge radius can significantly effect the initial airflow characteristic of the aerofoil section
11. Relative Airflow: If the wind has these three qualities then it is called to be relative airflow.
a. Direction: air parallel to and in opposite direction to the flight path of the a/c .
b. Condition: air close to but unaffected by presence of a/c, its temperature , velocity, and pressure not affected by the passage of a/c.
c. Magnitude: the magnitude of the Relative Air Flow is the TAS.
12. Effective Air Flow: if air does not possess all three of these qualities mentioned above it is referred as Effective Airflow.
13. Total Reaction: The resultant of all aerodynamic forces acting on the aerofoil section.
14. Centre of Pressure: The point on the chord line , through which lift is considered to be acting.
15. Lift: The aerodynamic force which acts at 90* to the Relative Air Flow.
16. Drag: The aerodynamic force which acts parallel to and in same direction of as of Relative Air Flow but in opposite direction of flight path.
17. Angle of attack/Aerodynamic Incidence: The angle between the chord line and Relative Airflow.
18. Effective angle of Attack: The angle between the chord line and the effective airflow is referred as the Effective Angle of Attack.