JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

Pre-Requisites

Nil

Course Objectives:

• Fundamental principle of airplane
• Theoretical Aerodynamics
• Aircraft application based on speed

Course Outcomes:

• Basic aerodynamic mechanics
• Effect of flow over wings

UNIT - I

Laws and Definitions: List the SI-units of measurement for mass, acceleration, weight, velocity, density, temperature, pressure, force, wing loading and power. - Define mass, force, acceleration and weight. - State and interpret Newton’s Laws. - State and interpret Newton’s first law. - State and interpret Newton’s second law. - State and interpret Newton’s third law. Explain air density. - List the atmospheric properties that effect air density. - Explain how temperature and pressure changes affect density. - Define static pressure. - Define dynamic pressure. - Define the formula for dynamic pressure. - Apply the formula for a given altitude and speed. - State Bernoulli’s equation. - Define total pressure. - Apply the equation to a Venturi. - Describe how the IAS is acquired from the pitot-static system. - Describe the relationship between density, temperature and pressure for air. - Describe the Equation of Continuity. - Define IAS, CAS, EAS, TAS

UNIT - II

Basics About Airflow: Describe steady and unsteady airflow. - Explain the concept of a streamline. - Describe and explain airflow through a stream tube. - Explain the difference between two and three- dimensional airflow.

UNIT - III

Aerodynamic Forces and Moments on Aerofoil: Describe the force resulting from the pressure distribution around an aerofoil. - Resolve the resultant force into the components ‘lift’ and ‘drag’. - Describe the direction of lift and drag. - Define the aerodynamic moment. - List the factors that affect the aerodynamic moment. - Describe the aerodynamic moment for a symmetrical aerofoil. - Describe the aerodynamic moment for a positively and negatively cambered aerofoil. - Forces and equilibrium of forces - Define angle of attack.

UNIT - IV

Shape of an Aerofoil Section: Describe the following parameters of an aerofoil section: - leading edge. - trailing edge. - chord line. - thickness to chord ratio or relative thickness. - location of maximum thickness. - camber line. - camber. - nose radius. - Describe a symmetrical and an asymmetrical aerofoil section. Wing shape: Describe the following parameters of a wing: - span. - tip and root chord. - taper ratio. - wing area. - wing planform. - mean geometric chord. - mean aerodynamic chord MAC. - aspect ratio. - dihedral angle. - sweep angle. - wing twist: - geometric. - aerodynamic. - angle of incidence.

UNIT - V

Subdivision of Aerodynamic Flow: List the subdivision of aerodynamic flow: - subsonic. - transonic. - supersonic flow. - Describe the characteristics of the flow regimes listed above. - Airplane for different speed and their applications.

TEXT BOOKS:

• 1. Stephen. A. Brandt, "Introduction to Aeronautics: A design perspective" American Institute of Aeronautics & Astronautics, 1997
• 2. Kermode, A.C., “Mechanics of Flight”, Himalayan Book, 1997

REFERENCE BOOK:

• 1. Anderson, J.D., “Introduction to Flight”, McGraw-Hill, 1995.