For supersonic and hypersonic wind tunnels, a diffuser efficiency, ηD,can be defined as the ratio of the total pressures at the diffuser exit andnozzle reservoir, divided by the total pressure ratio across a normal shockat the test-section Mach number. This is a measure of the efficiency ofthe diffuser relative to normal shock pressure recovery. Consider asupersonic wind tunnel designed for a test-section Mach number of 3.0which exhausts directly to the atmosphere. The diffuser efficiency is 1.2.Calculate the minimum reservoir pressure necessary for running thetunnel.

Q: Engineers call the supersonic combustion in a scramjetengine almost miraculous, “like lighting a…

A: Given Data: The area at section 1 and 4 is: A1=1 m2. The area at section 2 and 4 is: A2=0.2 m2. The…

Q: An aircraft with nose M1 P1 T1 properties of the upstream unifrom air M2 angle 0 = 15° as shown in…

A: nose angle θ = 15° Mach no M1 = 2.5 Upstream air pressure = P1= 60 kPa Upstream temperature = T1 =…

Q: (a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent…

A: In order to overcome this issue, we must address each component separately:(a): Relationship between…

Q: e end of the pipe. If the number, the mass flow

A:

Q: 3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is…

A: a. V=2832.61sm​,T0​=4219.872K,P0​=32962kPab. vs​=1303.87m/s, T0s​=77941K, P0s​=3392510kPac.…

Q: When operating at design conditions (smooth exit to sealevelpressure), a rocket engine has a thrust…

A: Write the given data.

Q: 1) What is the value of static temperature, stagnation temperature and stagnation pressure in the…

A: To calculatethe static temperature, stagnation temperature and stagnation pressure in the test…

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

A:

Q: Q2) Air (Y=1.4 and R=287 J/kg.k) flow through a converging - diverging nozzle designed to operate…

A: Air   Y = 1.4  R = 287 J/kg-K  d1 = 43 mm  d* = 25 mm  P1 = 86 kPA  T1 = 298 K  P2 = 12kPa

Q: For Air: y = 1.4 Question B1 a) With the aid of sketches give a clear account of the operation of…

A: To calculate the mass flow rate, calculate area ratio, back pressure drawing

Q: Air enters a constant-area duct at Mach 3 and stagnation conditions 1,000 K and 1.5 MPa. In the duct…

A: Given That:  Mach Number  = 3 Temperature = 1000 K Pressure = 1.5 MPa Mach number: The Mach number…

Q: At the entry of a diverging section, the temperature of a gas is 27*C, and the Mach number is 1.5.…

A:

Q: Problem 4. A converging-diverging nozzle, a with throat area of A = 10 cm?, is attached to a large…

A: Data given - At= 10cm2 Ae = 14 cm2 Po = 8 bar = 8×105 Pa To= 350 K r= 1.4

Q: (Q) A converging-diverging nozzle discharges an over-expanded jet into a room. Calculate the…

A:

Q: b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the…

A: Note:  5.198 is given in question by mistake. It must be 0.5198 for upstream mach.

Fluid Kinematics

The branch of science that deals with objects which are either in motion or stationary are studied under the branch of classical mechanics. Fluid mechanics is a subcategory of classical mechanics that deals with the behavior of fluids at rest (fluid statics) or in motion (posing some velocity). In fluid kinematics, studies focus on the associated motion of fluid particles or groups of particles, and its associated parameters like displacements, velocity, and acceleration without concerning about the forces that caused the motion. All the laws of classical mechanics are applied in the study of fluid kinematics.