30°C P.? Air 235 m/s tank 2 Mercury

Q: The tank in Fig.  is fi lled with water and has a venthole at point A. The tank is 1 m wide into the…

A: Understand that the tank accelerates to the right at 5 m/s2 and as the tank accelerates it causes…

Q: The pressure at a point on the wing of an airplane is 75.8kPa. The airplane istying with a velocity…

A: Solution is given under:

Q: . In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile…

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Q: Describe physically what the “speed of sound” represents.What kind of pressure changes occur in air…

A: Sounds travels as wave of energy by changing the motion of particles. The molecules of the air just…

Q: ir, at stagnation conditions of 450 K and 250 kPa, flows through a nozzle. At section 1, where the…

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Q: Q4. 1) The flow around a corner makes the edges of the expansion fan indicated by the angles as…

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Q: Q2 (a) In designing a nozzle why nozzle angle is not zero. Explain with the help of sketch. Q2 (b)…

A: Nozzle :- Nozzle is an device which are used to increase the kinetic energy and convert in to heat.…

Q: Prablen (t A large VacuuM tank, hetdat 6okAt abslute, Sucke searlevel standard qir throngh f…

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Q: The upstream flow properties are T1= 280 K and V= 2000 mph. What is downstream Mach number?

A: The Mach number, M, is defined as the ratio of the actual velocity V to the sonic velocity c, M=Vc…

Q: Compute stagnation enthalpy of air at normal conditions (P=1atm, T=300K) moving with velocity of…

A: Write the equation for the stagnation enthalpy. h0=h+v22   =CpT+v22 Here, The stagnation enthalpy is…

Q: Q1: when aircraft is ffying at subsonic velocity, the pressure at its nose i e. the stagnation point…

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Q: Q3: Uniform flow at Mach number equal (2) passes over a wedge of 10 half-angle, find M2, P2/P1,…

A: This problem is related to fluid mechanics. Fluid mechanics is the subject of mechanical engineering…

Q: A gas, assumed ideal, flows isentropically from point 1,where the velocity is negligible, the…

A: Hello. Since your question has multiple sub-parts, we will solve first three sub-parts for you. If…

Q: The large compressed - air tank shown in the figure bellow exhausts from a nozzle at an exit…

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Q: Design the 2D steady MOC contour for a super sonic nozzle assuming that the expansion section is a…

A: To design the 2D steady Method of Characteristics (MOC) contour for a supersonic nozzle, we need to…

Q: If the exit Mach number in Fig. is 2.2, what is theexit area?(a) 0.10 m2, (b) 0.12 m2, (c) 0.15 m2,…

A: Write the given data.

Q: In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile #…

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Q: 02: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit…

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Q: Suppose an aircraft is flying at standard sea-level at M = 0.8 and using a pitot-static tube for…

A: Given:The Mach number, The value of

Q: ir at P1 = 1 MPa, T1 = 600 °C and V1 = 150 m/s enters a converging nozzle. The exit area is A2 = 50…

A: A convergent nozzle is one that starts large and gradually gets smaller, resulting in a reduction in…

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

A: DISCLAIMER FOR MULTIPLE Since you have asked multiple questions, we will solve the first question…

Q: 4- Mach cone angle depend on the ...... Of the object., a- ambient temperature b- sound velocity, c-…

A: Mach cone angle is defined as μ=sin-11Ma where, Ma = mach number That is, Mach cone angle is a…

Q: The propagation of disturbances from a point source that results in an oblique shock wave can be…

A: sinμ =1M

Q: 1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a…

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Q: In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile #…

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Q: The pressure at a point on the wing of an airplane is 75.8kPa. The airplane isying with a velocity…

A: The solution is given below:

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: Q4//B/ Heat is removed from airflow in a constant-area duct, if flow enters at Mach 2.20, Ti= 310 K,…

A: Stagnation Point: The point in the flow where fluid velocity will be zero is called the stagnation…

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: est section. Find the temperature and pressure in the test section and the upstream K kPa K

A: The mach number given as .The velocity given as .The density given as .

Q: Consi der a shockwave with an angle of ß= 25° that impinges on a wall at point p (as shown in the…

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Q: In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile #…

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Q: In the figure below, the surface pressure coefficient at point Q on the fuselage of the projectile #…

A:

Q: The pressure at a point on the wing of an airplane is 75.8kPa. The airplane isying with a velocity…

A: Atmospheric properties at 3280 yards are notes. a) Formula Cp = pressure difference/ dynamic…

Q: An experimental scramjet aircraft is flying at an altitude of 25,000m at Mach 5. Considering it;s…

A: Given: M1 =5  delta = 5 deg P2/P1 = ?

Q: Example (3-5): Air flow through a duct with constant area. At inlet point of the duct the flow…

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