Define Airfoil. Difference between Airfoil and Wing.
[3 marks]With neat sketch explain Airfoil nomenclature.
[4 marks]Explain Airfoil characteristics with appropriate graph.
[7 marks]Define Vortex filament.
[3 marks]Consider NACA 2414 airfoil with a chord of 0.64 m in an airstream at standard sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1254 N/m. Calculate the co-efficient of lift.
[4 marks]Derive Linearized velocity potential equations.
[7 marks]Prove the relation ‘Local jump in tangential velocity across the vortex sheet is equal to the local sheet strength” using vortex sheet.
[7 marks]What is the physical phenomena of V =Vin Kutta Condition?.
[3 marks]Without friction could we have Lift? Explain properly
[4 marks]Explain with neat sketch Kelvin’s circulation theorem.
[7 marks]Define Downwash and Induced drag.
[3 marks]Explain stream function with equations.
[4 marks]Prove the relation “Camber line is a streamline of the flow” in thin airfoil theory.
[7 marks]Define Biot-Savart Law with equation.
[3 marks]Draw and explain an elliptic lift distribution.
[4 marks]Explain with appropriate equation Prandtl’s Classical Lifting Line theory.
[7 marks]Define 1. Aspect ratio 2. Compressible flow
[3 marks]Explain General lift distributions with appropriate equations.
[4 marks]Explain with “Lift Curves for an infinite wing versus a finite elliptic wing”.
[7 marks]Difference between subsonic and supersonic flow.
[3 marks]Define Critical Mach number with appropriate equation.
[4 marks]Derive Prandtl Glauert Compressibility corrections rule.
[7 marks]Using Linearized theory, calculate the lift coefficient for a flat plate at a 50 angle of attack in a Mach 3 flow.
[3 marks]Draw “Linearized supersonic flow over an airfoil”.
[4 marks]Derive with neat sketch “Numerical vortex panel method equation”.
[7 marks]