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Flight Mechanics

Flight mechanics course will helps students understand aircraft motion, stability, control, and performance, forming the foundation for safe, efficient aerospace design and operations.

Course Outcome

This course is designed to equip studuents with the principles of aircraft motion, forces, and moments; analyze stability and control; understand performance in various flight regimes; apply equations of motion; interpret aerodynamic effects; and solve practical flight mechanics problems relevant to aircraft and UAV design and operation.

Pedagogical Approaches

Animated content, 3D Simulations, and Video lecture integrations

Prerequisite Subjects

Engineering Mathematics, Engineering Mechanics.

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Syllabus
Learning Modules
Experiments
Test Your Knowledge
References
Syllabus
Basics of Flight Mechanics — Syllabus

Module 1: International Standard atmosphere

Module 2: Classification of aircraft

Module 3: Airplane configuration

Module 4: Primary flight instruments

Module 5: Aerodynamic forces and moments

Module 6: Drag polar

Module 7: Airplane performance

Module 8: Longitudinal Static stability

Module 9: Lateral & Directional Static stability

Module 10: Dynamic stability

Learning Modules
Atmosphere by Dr Aishwarya Dhara
Aircraft components by Dr Aishwarya Dhara
Dynamic stability by Dr Aishwarya Dhara
Experiments

Virtual Lab

Aim
To investigate the effect of aerodynamic forces (Thrust, Lift, Drag), mechanical constraints (Friction, Weight), and pilot input (Rotation time, Load factor) on the total takeoff distance of an aircraft.
Apparatus / Tools

Good internet connectivity

Scientific Calculator: For manual verification of kinematic equations.

Formulae & Governing Equations
The takeoff is analyzed as the sum of three distinct horizontal distances: $$S_{TO} = S_g + S_{rot} + S_{tr}$$
PhaseFormulaKey Variable
Ground Roll (Sg) \( S_g = \frac{V_{TO}^{2}}{2a} \)
\( a = \frac{g}{W}[T - D - \mu(W-L)] \)
Acceleration \(a\)
Rotation (Srot) \( S_{rot} = V_{TO} \cdot t_{rot} \) Rotation time \(t_{rot}\)
Transition (Str) \( S_{tr} = R \cdot \sin(\gamma) \)
\( R = \frac{V_{TO}^{2}}{g(n-1)} \)
Load factor \(n\)
Climb Angle (γ) \( \sin(\gamma) = \frac{T-D}{W} \) Excess Thrust \(T-D\)
Theory & Concepts
Takeoff performance is a balance between Energy Addition (Thrust) and Energy Dissipation (Drag/Friction).

Acceleration Phase: The aircraft must overcome static and rolling friction. As speed increases, Lift (L) reduces the effective weight on the wheels, reducing friction but increasing aerodynamic drag (D).

Rotation: The point where the nose gear leaves the ground. A longer rotation time increases the horizontal distance significantly without gaining altitude.Transition Geometry: The aircraft follows a circular arc. The radius (R) of this arc depends on the "pull-up" load factor (n). A higher n results in a tighter turn but requires more structural strength and pilot skill.

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References

1.

Skyify
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