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Flashcards in M1 Deck (52):
1

Bernoulli's Equation

ONLY FOR INVISCID INCOMPRESSIBLE FLOW

2

inviscid compressible flow

density changes
kinetic energy changes
internal energy changes
Euler's equation MUST be used

3

inviscid (def)

frictionless

4

incompressible (def)

density is constant

5

what remains constant in incompressible flow?

temperature and density

6

isentropic flow

adiabatic and inviscid

7

what states are variable during compressible flow

pressure, density, temperature, velocity

8

entropy (def)

measure of energy of the system that is unavailable to produce work

9

enthalpy (def)

measure of heat content of system

10

adiabatic (def)

without gain or loss of heat

11

isentropic (def)

without gain or loss of entropy

12

homogenous (def)

density and composition are the same throughout

13

specific heat (def)

measure of heat capacity fo system

14

stagnation condition (def)

when flow is stopped isentropically and adiabatically (KE converted to heat or pressure)

15

reversible (def)

no friction

16

the mach number for oblique and normal shock waves

greater than 1

17

downstream mach number for normal shockwave is always

smaller than 1

18

a pitot tube measures the

total pressure, static pressure, air speed on aircraft

19

static pressure (measures)

only random motion of gas

20

total pressure

flow is isentropically decelerated to zero velocity

21

combination of total pressure and static pressure allows one to measure

velocity at a certain point

22

constant entropy implies conservation of throughout system

conversation of energy

23

shock wave (def)

thin region of highly viscous flow, a propagating disturbance when a wave moves faster than the speed of sound

24

flow through shock wave is

adiabatic but nonisentropic

25

energy is what across shock wave?

conserved

26

synonym for shock wave

propagating disturbance (PD)

27

when a wave moves faster than the speed of sound in a fluid

it's called a shock wave

28

shock wave is characterized by

abrupt discontinuous change in pressure, temperature, density

29

if M>0.3

flow is compressible

30

adiabatic gas is what kind of gas

calorically perfect gas

31

total temperature is across stationary normal shock wave

constant

32

velocity and total pressure across normal shock wave

decrease

33

normal shock is

adiabatic, nonisentropic

34

normal shock equations are a function of only

M1

35

mach number behind shock wave is always

smaller than one

36

velocity and total pressure across normal shock wave

decrease

37

density, sPressure, and temperature across normal shock wave

increase

38

as M1 increases, p0,2/p0,1

decreases

39

total pressure is an indicator of how much

useful work can be done by a flow

40

sound wave is, but not isothermal

IS ADIABATIC

41

speed of sound travels 20x than in air

faster

42

for given upstream M1, there is a

maximum deflection angle theta max

43

if theta>theta(max)

no solution exists for straight oblique shock, curved detached shock wave

44

value of theta max increases as M1

increases

45

at higher Mach numbers, the straight oblique shock solution can exist at

higher deflection angles

46

for any give theta less than theta max

two straight oblique shock solutions for a given upstream M exist

47

smaller value of beta is called

weak shock solution

48

larger value of beta is called

strong shock solution

49

for strong solution, M2 is always

subsonic

50

for weak solution, M2 is usually

greater than 1

51

for theta values very close to theta max,

M2 is less than one

52

if theta = 0

beta equals 90 degrees