Karunya Advanced Aerodynamics Question Bank 2025
Download Karunya Institute of Technology and Sciences, Advanced Aerodynamics [21AE3001] Question Bank Nov/Dec 2025 PDF Free Online.
Download Karunya Advanced Aerodynamics Question Bank 2025
| Advanced Aerodynamics [21AE3001] | Download Here |
Karunya Advanced Aerodynamics Questions
Part – A : (5 X 16 = 80 Marks) (Answer any five from the following)
1. a. Describe how the principle of mass conservation leads to the continuity equation for incompressible and compressible flows. CO1 U
b. Interpret the relationship between stress and strain rate in a Newtonian fluid and explain the role of Stokes’ hypothesis in simplifying this relationship. CO1 U
2. a. Define fully developed flow and state the conditions under which flow is considered fully developed in a pipe or channel. CO2 A
b. Define Poiseuille flow and discuss the important characteristics of laminar flow between two immiscible fluid layers in a horizontal channel. CO2 A
3. a. Explain how the order of magnitude approach can be used to simplify the Navier-Stokes equations for a steady, incompressible flow over a flat plate within the boundary layer region. CO3 A
b. Using the integral form of the momentum equation, calculate the friction drag on a flat plate and explain how boundary layer separation influences the result. CO3 A
4. a. Define compressibility. Derive the expression for the velocity of sound in an ideal gas. CO4 An
b. Define pressure coefficient and discuss the corrections applied to a Pitot-static tube for subsonic and supersonic flow measurements. CO4 An
5. a. Compare normal shock, oblique shock and expansion wave with suitable examples. CO5 A
b. Derive the governing equations to determine the shock Mach number and pressure ratio in a shock tube for given initial driver and driven gas pressures. CO5 A
6. a. Explain how the first law of thermodynamics is applied to compressible flow and describe the basic concept of pressure wave propagation in a gas medium. CO4 U
b. Explain the effect of back pressure variation on the flow through a nozzle and describe the conditions for the formation of normal and oblique shocks. CO4 U
7. a. Describe the Prandtl relation and Hugoniot equation for a normal shock and explain their significance in compressible flow analysis. CO5 U
b. Explain the difference between a propagating shock wave and a reflected shock wave with neat sketches. CO5 U
Part – B : (1 X 20 = 20 Marks) [Compulsory Question]
8. a. Analyze how friction influences the flow parameters (pressure, temperature, density, and Mach number) along a constant-area duct. Use the governing Fanno flow equations to illustrate how the flow evolves from supersonic to subsonic conditions. CO6 An
b. Using the Rayleigh flow relations, analyze the condition for maximum heat transfer and interpret the physical significance of this condition in terms of changes in Mach number and flow direction (subsonic/supersonic). CO6 An
Course Outcomes:
• CO1-Assess the forces and moments due to flow
• CO2-Understand the flow behavior over various body shapes
• CO3-Apply compressibility corrections for flow in C-D passages and instruments like Pitot static tube
• CO4-Assess the nature of compressible flow over airfoils and finite wings
• CO5-Use the computational tools to evaluate hypersonic flows
• CO6-Understand the basic principles of expansion waves
