Gas Dynamics KA

for a normal shock: mach

supersonic to subsonic

for a normal shock what increases

static pressure, static temperature, and density

for a normal shock what decreases

mach, velocity, and stagnation pressure

for a normal shock what stays the same

total temperature and area

for subsonic Raleigh flow what increases

mach, velocity, static temperature, and total temperature

for subsonic Raleigh flow what decreases

static pressure, density, and total pressure

for supersonic Raleigh flow what increases

static pressure, static temperature, density, and total temperature

for supersonic Raleigh flow what decreases

mach, velocity, and total pressure

for subsonic Fanno flow what increases

mach and velocity

for subsonic Fanno flow what decreases

static pressure, static temperature, density, total pressure

for supersonic Fanno flow what increases

static pressure, static temperature, and density

for supersonic Fanno flow what decreases

mach, velocity, and total pressure

for Prandtl-Meyer what increases

mach, velocity

for Prandtl-Meyer what decreases

static pressure, static temperature, density, and and mach angle

for Prandtl-Meyer what stays the same

total pressure and total temperature

for oblique shock what increases

static pressure, static temperature, and density

for oblique shock what decreases

mach, velocity and total pressure

for oblique shock what stays the same

total temperature and area

for normal shock use table

A.1 & A.2

for Rayleigh flow use table

A.3

for Fanno flow use table

A.4

for Prandtl-Meyer use table

A.5

for Oblique shock use chart

theta-beta-M

for straight flow

normal shock problem

for wedges/ramps

oblique shock chart

nozzle diffuser with area changes and no loss

isentropic tables

constant area and heat addition

Rayleigh tables

constant area and friction

Fanno tables

supersonic flow turning away from itself

Prandtl-Meyer table

supersonic flow turning into itself

oblique shock chart