3 Credit Hours

Fundamentals of inviscid and viscous hypersonic flowfields. Classical and modern techniques for calculating shock wave shapes, expansions, surface pressures, heat transfer and skin friction. Applications to high speed aircraft, rockets and spacecraft.

Prerequisites

MAE 351: Aerodynamics II, MAE 553: Compressible Fluid Flow, or equivalent course in compressible flow.

Course Objectives

You will be expected to apply your knowledge of compressible fluid dynamics and thermodynamics to the high Mach number regime. You will evaluate flow features such as shockwave shapes, stagnation point regions, and boundary layer growth. You will assess the forces and heating experienced by vehicles in both glide and atmospheric reentry. Some specific learning outcomes are listed below:

• Identify the aerothermodynamic differences between supersonic flow and hypersonic flow.
• Compute the lift and drag coefficients on specified geometries exposed to hypersonic flow.
• Evaluate the pressure field generated by shock interactions and reflections at high Mach numbers.
• Solve for the velocity and temperature profiles within hypersonic boundary layers.
• Assess the effect of viscosity on the surface properties of a vehicle flying at high Mach numbers.
• Develop and optimize a wave rider geometry for specified Mach numbers and shock angles.

Course Requirements

Component	Percentage
HW Assignments	20%
Project(s)	25%
Midterm Exam	25%
Final Exam	30%

Textbook

None required.
Optional: Anderson, J. D., Jr. (2006). Hypersonic and High-Temperature Gas Dynamics (2nd ed.). American Institute of Aeronautics and Astronautics.

Created: 11/17/2025.