MAE 3293 · Oklahoma State University
Fundamentals of Aerodynamics
Interactive lessons for MAE 3293, Fundamentals of Aerodynamics, at Oklahoma State University. Each lesson pairs the derivations with figures computed live from the exact relations for a calorically perfect gas: change the Mach number, the geometry, or the back pressure and the wave pattern, the pressure distribution, and the forces update at once. The lessons follow Kursat Kara’s lecture notes and J. D. Anderson, Fundamentals of Aerodynamics.
Compressible flow
Lessons
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Chapter 9
Oblique Shock and Expansion Waves
Mach waves, the θ–β–M relation, shock reflection, Prandtl–Meyer expansion and isentropic compression, and shock-expansion theory for flat-plate, wedge, and diamond airfoils.
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Chapter 10
Nozzles, Diffusers, and Wind Tunnels
Quasi-one-dimensional flow: the area–velocity and area–Mach relations, choked flow, converging-diverging nozzles with normal shocks inside or at the exit, rocket thrust, diffusers, and supersonic wind-tunnel start-up.
For homework and exams
Calculators
- Compressible Aerodynamics Calculator
Isentropic flow, normal and oblique shocks, Prandtl–Meyer expansion, and wedge airfoils: enter one known quantity and read the rest, in place of the tables in Anderson’s appendices.
- Supersonic airfoils
Shock-expansion theory for flat-plate, wedge, and diamond airfoils, compared with linear (Ackeret) theory, with lift, wave-drag, and moment coefficients over a range of angles of attack.
Notes
Using the lessons
Each lesson is a single self-contained web page. The equations, fonts, and figures are built in, so a lesson keeps working with no network connection once it has loaded; save the page in the browser to keep a copy on a laptop or tablet.
The ratio of specific heats, γ, in the top bar of each lesson applies to every figure on that page. The theme and text size follow the setting chosen on the calculator.
Corrections and suggestions are welcome through the issue tracker.