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: 5-Which of the following is true for a Fanno flow (a) The Mach number always increases as one moves…

A: Which of the following is true for Fanno flow. Answer: (c) The maximum length of the duct is the…

Q: 1. For a symmetric airfoil, the lift coefficient for zero-degree angle of attack is (c) 0.5 (а) -1.0…

A: As per our company policy we are asked to 1 question or 3 subpart only.. I am solving 1-4 ..please…

Q: What is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude? 1.59 6.02…

A: Given :-  Airflow velocity = 2000 m/s Altitude = 2000 ft To Find :-  Mach Number (M)

Q: For a converging-diverging nozzle that is choked what is the ratio of nozzle area divided by the…

A:

Q: Determine the ini tial Mach number, exit pressure ,exit temperature and stagnation pressure loss if…

A:

Q: In March 2004, NASA successfully launched an experimental supersonic-combustion ramjet engine…

A: Given Data: The Mach of the scramjet is: M=7 The temperature is: T=-45 °F

Q: A fuel–air mixture, assumed equivalent to air, enters a ductcombustion chamber at V1 = 104 m/s and…

A: Given: The initial temperature,T1 300 K The initial velocity, V1=1.4 m/s Solution:

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

A: Write the given data.

Q: A subsonic inlet diffuser of area ratio 3 is employed in a Mach-2 jet engine. A normal shock is…

A: Normal shock at inlet and in downstream region isentropic relations are used to arrive the solution.

Q: What is the Mach Number of an air with a velocity of 250 m/s, at a temperature at 2800 meters?

A: Solution: Speed of sound at 2800m=329m/s  (from gas table for compressible flow data book) Mach…

Q: [5] An experimental centrifugal compressor is fitted with free-vortex guide vanes in order to reduce…

A:

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

A:

Q: Heat is rejected from the air flowing in a constant area duct. At the duct entrance, the air is…

A: Rayleigh flow and isentropic relations are used to arrive the solution.

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: Consider a cone at zero angle of attack in a hypersonic flow. (Hypersonic flow is very high-speed…

A: The provided cone has the symmetry about its rotational axis. Consider a coordinate system with the…

Q: Q9: A normal shock wave is propagated into still air with a velocity of 722.4 m/s. The still air…

A: "Since you have posted a question with multiple sub-parts, we will solve first three sub parts for…

Q: a given point in a flow field or air, Mach number, velocity, and density are 0.9, 300 mps, and 1.2…

A: we have to determine the dynamic pressure of this flow

Q: Consider a hypersonic vehicle with a spherical nose flying at Mach 20at a standard altitude of…

A: Given Data: The ambient temperature is T∞=500°R. The ambient pressure is P∞=3.06 lb/ft2. Nose…

Q: the upstream Mach number, an oblique shock wave with W = 4. Determine considering 32° and a pressure…

A: A dimensionless quantity which represents the ratio berween the local flow velocity of the object in…

Q: Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.5. If the…

A: Given data P1=10 psiaT1=440.5 R

Q: Air flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock…

A: Given: Mach number at section 1,Ma1=2.5 The pressure at section 1,p1=40 kPa The temperature at…

Q: Under low-speed incompressible flow conditions, the pressure coefficientat a given point on an…

A: Given data Cp0=-0.54M=0.58

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: A supersonic nozzle is used for discharging air from a reservoir. The reservoir pressure and…

A: normal shock and isentropic relations are used to arrive the solution.

Q: 11.47 At a certain point in a pipe, air flows steadily with a velocity of 150 m/s and has a static…

A: Given Data The velocity of air is:v=150 m/s The static pressure is:P=45 kPa The static temperature…

Q: When the Apollo command module returned to earth from the moon, itentered the earth’s atmosphere at…

A: Given data The mach number is M=36 The free-stream temperature is T∞=300 K The ratio of specific…

Q: 01 : The velocity, pressure, and temperature at a certain point in a steady air flow, are 600 m/s.…

A: Given data: -  The velocity of air at a certain point is v = 600 m/s. The pressure of air at a…

Q: 2) Prove that the mass of gases (m) flowing in the convergent-divergent nozzle of an afterburning…

A: Mass flow rate= m˙M= mach number P0= Total pressure T0= Total temperature A= area γ= specific heat…

Q: Consider the air flow over the wing of a civil airliner flying at M, 0.85 and at an altitude of…

A: Free stream mach number = 0.85 (given) Isentropic relations are used to arrived the solution.

Q: AQ2) Air (y = 1.4) flows into a constant-area insulated duct with a Mach number of 0.20. For a duct…

A:

Q: When a pitot tube such as in Fig.  is placed in asupersonic flow, a normal shock will stand in front…

A: Given data: The Mach number inside the shock can be determined as,

Q: Air enters a rectangular duct at T1 = 285 K, P1 = 390 kPa, and Ma1 = 2. Heat is transferred to the…

A: The static temperature at the inlet of the duct is T1=285 K. The inlet pressure of the duct is…

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

A: A spout is a somewhat straightforward gadget, simply an exceptionally formed tube through which hot…

Q: The flow inside the intake of a scramjet is found to be supersonic with Mach number of 2.5. From the…

A: Given: The Mach number, M1 = 2.5 The static pressure, P1 = 1 atm The static temperature, T1 = 290 K…

Q: Air flows steadily from a tank through the pipe inFig. . There is a converging nozzle on the end.…

A: For the given mass flow rate of 3 kg/sec determine a) Mach number at section 1b) The pressure…

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: QS. Air with stagnation conditions of 35 bar and 450 K enters a combustion duct via a…

A: given data; ⇒air at stagnation condition;⇒stagnation pressure(P0)=35bar⇒stagnation…

Q: A turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to…

A: Given: M1 = 1.09 k = 1.35 P1 = 280 kPa T1 = 586 K

Q: A gas which has a molar mass of 39.9 and a specific heat ratio of 1.67 is dis- charged through a…

A:

Q: Q1) Air at mach number 2 over a wedge and generation of an oblique shock wave 40° . determine : 1.…

A:

Q: For low-speed (nearly incompressible) gas flow, the stagna- tion pressure can be computed from…

A: Assumption 1) Non-Viscous 2) Adiabatic 3) Isentropic 4) Steady flow

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

A:

Q: 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle…

A: Given  M1=2σ=40°P1=50kpaT1=273k

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

A: Stagnation point: The point at which the velocity of the fluid becomes zero. When the fluid is…

Q: Air enters a rectangular duct at T₁ = 300 K, P₁ = = 420 kPa, and Ma₁ = 2. Heat is transferred to the…

A: Given data as per question  T₁ = 300 K P₁ = = 420 kPa  Ma₁ = 2 Heat is transferred to the air =55…

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.