WorksheetsCOMPRESSIBLE FLUID FLOW
Total questions: 20
Worksheet time: 15mins
Mach Number is the ratio of
square root of inertia force to viscous force
inertia force to elastic force
square root of inertia force to Elastic force
square root of inertia force to pressure force
A vehicle is moving at 1400 km/hr(air,Temp=37 degree)
Vehicle travelling at supersonic speed
Vehicle travelling at sonic speed
Vehicle travelling at sub sonic speed
Vehicle travelling at hypersonic speed
IDENTIFY THE EQUIPMENT
VENTURIMETER
ANEMOMETER
WIND TUNNEL
AIR TUNNEL
The definition of flow being compressible is
Depends on precision required
M > 0.5
M > 0.3
Prandtl relation for normal shock waves is
a^2=u1u2
a^*2=u1u2
a*a0=u1u2
Select the false statement for the normal shock wave.
Entropy increases across normal shock wave
Normal shock wave has velocity and pressure gradients
Shock wave is pretty thick
The impulse function is given by
F = p*A + (density)*A*(V^3)
F = p*A + (density)*A*sqrt(V)
F = p*A + (density)*A*V
F = p*A + (density)*A*(V^2)
Compressible flow mainly deals with
Solid dynamics
Liquid dynamics
Gas dynamics
Solid and liquid dynamics
Which one of the following is proper for a normal shock wave?
Reversible
irreversible
For a compressible flow mach number must be
less than 0.3
equal to 0.3
Greater than 0.3
Stagnation Temperature is constant for
isentropic flow,
across the Shock
Fanno Flow
All of the above
"Shock waves are always present in subsonic region".
True
False
P*,T*,C* means
State of gas at M=1.2
State of gas at M=0.3
State of gas at M=1
State of gas at M=0.8
in compressible fluid flow problems state of gas at reservoir is taken as
static condition
stagnation Condition
Critical condition
if (A exit/A*) value of a convergent divergent nozzle is 3 then mach number at exit?
2.64
0.2
if (A exit/A*) value of a convergent divergent diffuser is 3 then mach number at exit?
2.64
0.2
Mx ,My,T0,T* identify correct answer
Downstream mach number,Upstream Mach number,stagnation Temperature,static temperature at M=1
Upstream mach number,downstream Mach number,stagnation Temperature,static temperature
Upstream mach number,downstream Mach number,stagnation Temperature,static temperature at M=1
Upstream mach number,downstream Mach number,stagnation Temperature,static temperature
In shock tables Mx<My
True
False
Fanno flow deals with
flow with friction & without heat transfer
flow without friction & with heat transfer
Rayleigh flow is deals with
flow without friction & with heat transfer
flow with friction & without heat transfer
