flowchart TD
aim(["<b>Aim</b>: Calculate L, D, M for <b>low subsonic</b> aircraft (wing)"])
fm0(["Basic terminology of airfoil/wing"])
fm1(["3D Viscous Compressible Conservation equations <br>(integral/differential)"])
euler(["Euler's equation"])
bernouli(["Bernoulli's equation: Integration of <br>Euler equations under various conditions"])
potential(["Potential flow equation"])
aim -->|Review|fm1
aim -->|Review|fm0
fm1 -->|Inviscid Assumption|euler
euler -->|Irrotational Assumption|potential
euler -->bernouli
fdm(["Finite Difference Methods"])
sm(["Singularity Methods"])
panel(["Panel Methods"])
elementary(["Elementary solutions<br/>source/doublet/vortex"])
vortex(["Vortex tube/Helmholtz theorems<br/>line vortex/vortex sheet"])
kelvin(["Kelvin's Circulation Theorem"])
kj(["Kutta-Joukowski Theorem"])
tat(["Thin airfoil theory"])
lvm(["Lumped vortex method"])
llt(["Prandtl lifting line theory"])
<!--
potential -->|Review|elementary
potential -->|Domain discretisation|fdm
potential -->sm
potential-->vortex
sm -->panel
sm -->|Analytical Solution 2D|tat
sm -->|Analytical Solution 3D|llt
vortex -->panel
vortex -->tat
vortex -->llt
tat -->lvm
lvm -->llt
app(["Applications"])
delta(["Delta Wings"])
cs(["Control Surfaces/flaps"])
pitot(["Pitot tube"])
aim -->app
app -->delta
app -->cs
app -->pitot