3 credits
Fall 2026 Lecture Distance Learning Upper Division
Incompressible airfoil and lifting line theory. Steady and unsteady, one-dimensional, linear and nonlinear flows. Normal and oblique shock waves. Isentropic expansions. Steady, supersonic, two-dimensional linear and nonlinear flow applied to airfoils. Linear subsonic compressible flow for airfoils. Design applications.
Learning Outcomes1Calculate thin airfoil performance parameters for incompressible flow.
2Utilize lifting line theory to analyze wings and determine parameters such as lift coefficient, induced drag coefficient, and/or wing loading.
3Perform static longitudinal stability analyses to determine if a wing-horizontal tail configuration is stable and/or trimmable and explain the impact of design variables on the longitudinal stability of an airplane.
4Predict the variation of properties in a converging-diverging nozzle under subsonic and supersonic conditions.
5Determine supersonic airfoil performance by shock-expansion theory.
6Determine supersonic airfoil performance by linearized supersonic theory.
7Apply subsonic compressibility corrections for airfoils to incompressible results.
8Describe the impact of airfoil geometry and wing geometry on the determination of the critical Mach number.
Prerequisites
GPA by professor
made by Purdue students.