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: Asap.. An isentropic flow through a convergent-divergent nozzle with an exit-to-throat ratio of…

A: The ratio of exit area to throat area is The flow through the throat is subsonic.The exit pressure…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Given: To = 2000+273 = 2273 K Po = 5 MPa Correct option: 1100 m/s

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: Determine the critical mach number according to linear theory

A: Given          Local mach number, MA = 0.435 Streamline mach number, M0 = 0.3 Find Critical mach…

Q: A perfect gas (gamma = 1.9) enters a converging-diverging nozzle with a Mach number of 0.98 and…

A: Given: The specific heat ratio, n = 1.9 The inlet Mach number, M1 = 0.98 The local pressure, P1 =…

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: A long pipe of 0.0254 m diameter has a mean coefficient of friction of 0.003. Air enters the pipe at…

A: This question is solved by the Mach number relation, To1T1=1+γ-12M12 M1 is the enter Mach number, T0…

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: 2- Conditions before a shock are T1 = 40°C, pl = 1.2 bar, and M1 = 3.0. An oblique shock is observed…

A:

Q: The SR-71 Blackbird is the fastest production plane capable of reaching speeds of more than Mach 3,…

A: GivenMach no. for blackbird M=3specific heat of air R=287j/kg.kspecific heat ratio γ=1.4To…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Givenstagnation temperature = 2000 deg C stagnation pressure = 5 MPa exit temperature = 909 K

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: Suppose a gas flows through a constant insulated path. Parameters of temperature, pressure and mach…

A: given; ⇒initial temperature(T0)=520R⇒initial pressure(P0)=50psi⇒mack number (M0)=0.45⇒at…

Q: A long pipe of 25.4 mm diameter has a mean coefficient of friction of 0.003. Air enters the pipe at…

A: Given Data Diameter of pipe, d=25.4 mm = 0.0254 m Mach number, M=2.5 Coefficient of friction,…

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: Consider supersonic airflow approaching the nose of a two-dimensional wedge at a Mach number of 3.…

A: Given data: The Mach number of the flow is M = 3.

Q: Q1: Air expands from a storage tank through a converging diverging nozzle having a hroat area of (70…

A: Given:The throat area is .The shock area is .The exit area is .The pressure and temperature is  and…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Given: Let us consider the given, Stagnant Temperature, T0=2000°C+273=2273 k Exit temperature,…

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: A supersonic diffuser for air (y%3D1.4) has an arca ratio of 0.416 with an inlet Mach number of 2.4…

A:

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.

Q: A perfect gas (y = 1.4) enters a converging-diverging nozzle with a Mách number of 0.50 and local…

A: gama =1.4 inlet mach number (M1) =0.5 Inlet velocity (V1) = 165 m/s  P1 =280 KPa T1 = 280 K Throat…

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.