Consider an oblique shock wave with a wave angle of 30◦ in a Mach 4flow. The upstream pressure and temperature are 2.65 × 104 N/m2 and223.3 K, respectively (corresponding to a standard altitude of 10,000 m).Calculate the pressure, temperature, Mach number, total pressure, and totaltemperature behind the wave and the entropy increase across the wave.

Q: A large tank supplies helium through a converging-diverging nozzle l8 atmosphere. The Pressure in…

A: Nozzle : Nozzle is a duct or a pipe which controls the flow of fluid. Generally it is of two types…

Q: A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge (Fig. 10E.1). An oblique…

A: supersonic air flow travelling at passes over a wedge,T1=-10o CT1=263.15 KFrom table at Mach,…

Q: 5. The upstream Mach number for a given Prandtl-Meyer expansion is 3.2 and the pressure ratio…

A: When an amount of force act on the surface of the object in perpendicular direction what has the…

Q: Supersonic air at Ma1 = 2.0 and 230 kPa flows parallel to a flat wall that suddenly expands by ? =…

A: Assumption The flow is steady The boundary layer on the wall is very thin Properties: The fluid…

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

A: Given-Data:-V=722.4m/sP1=1atm=1.0133×105N/m2T1=294.4K To-Find:- 1) Mach number2) Pressure 3)…

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

A:

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: A piston moves along a tube containing air at an initial sound speed of 330 m/s. When the piston…

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Q: A supersonic aircraft flies with a speed of 2750 km/h at 27 °C and 100 kPa weather conditions. Two…

A: Note :- you have posted multiple questions on single window. As per the guidelines I am able to…

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

A:

Q: Calculate the change in Temperature (T2) after a cooled Helium gas with velocity (v1) and speed of…

A: Given data Speed of Helium = v1 = 642.78 m/sSpeed of sound = va1 = 360.51 m/s

Q: An air stream, with T1 =0 C, p1 = 60.0 kPa (abs), and V 497 m/sec, undergoes a normal shock.…

A:

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: vortex generators on the upper surface of a wing will

A: Vortex generators on multiengine aircraft increase controllability at low airspeeds and reduce…

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

A:

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: A convergent-divergent nozzle with an exit-to-throat area ratio of 1.616has exit and reservoir…

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

A: Given data Cp0=-0.54M=0.58

Q: Air in a large tank is at a pressure of 800 kPa and a temperature of 300 K. It is expanded through a…

A: Given,  Inlet pressure to the convergent-divergent nozzle is, P0=800 kPa Inlet temperature to the…

Q: At a given point in a supersonic wind tunnel, the pressure and temperature are 5 x 10* N/m and 200…

A: Given: Static pressure P=5×104N/m2 Static temperature T=200K Stagnation pressure P0=15×106 Solution:…

Q: 5. Air at stagnation pressure of 600 kpa and stagnation temperature of 530 K enters a frictionless…

A: Give:- Pox = 600Kpa, Tox = 530K, At = 5 cm2, Ae = 12.5 cm2, Pe = 300Kpa. To Find:- Pb,e = ?

Q: Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number…

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Q: Explainwhat do you understand by the term “Compressibility Corrections” for thin airfoils in high…

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Q: Air flows isentropically in a channel. Properties at section1 are V1 = 250 m/s, T1 = 330 K, and p1 =…

A: a) The expression for the isentropic flow is: Here, P2 represents the pressure at section 2, P1…

Q: Fuel is to be burned in a stream of air moving with a Mach No. 2.0, a temperature (-160 F), and a…

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Q: e Tr1 = 650°R and q* = 500 BTU/lbm, respectively. Calculate a) the inlet Mach number Mị b) exit…

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Q: Q1: Air enters a converging-diverging nozzle having throat diameter of 8.5cm and exit diameter 28cm.…

A: Given,  Throat diameter, dT=8.5cm=0.085 m Exit diameter, dE=28cm=0.28m The cross-sectional area of…

Q: Air, with stagnation conditions of 800 kPa and 100°C, ex pands isentropically to a section of 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: An air nozzle has an exit area 1.6 times the throat area. If a normal shock occurs at a plane where…

A: It will be assumed that the supply tank is large enough to be able to assume that the tank pressure…

Q: Air with initial stagnation conditions of 700 kPa and 330 K passes through a convergent-divergent…

A:

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: 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: A wind tunnel nozzle is designed to yield a parallel uniform flow of air with a Mach number of 3.0.…

A: Given: Pe = 100 kPa Po = 7000 kPa

Q: 1. Air (y=1.4) enters a converging-diverging nozzle from a reservoir which is at a pressure of 300…

A:

Q: At the point where the air enters the convergent nozzle, its static pressure is 150 kPa, its…

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Q: Q11: Air enters the converging section shown in Figure and a normal shock occurs at the exit. The…

A:

Q: Nitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and…

A: Given: Initial pressure, P01=620 kPa Initial temperature, T01=310 K Upstream Mach no., Ma1=3…

Q: 21: Air enters a converging-diverging nozzle having throat diameter of 8.5cm and exit dian 8cm. the…

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Q: Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over a wedge which…

A:

Q: Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1).…

A:

Q: Air enters a converging–diverging nozzle of a supersonic wind tunnel at 150 psia and 100°F with a…

A: Temperature at the test section  Ttest=T01+k-12Ma2=5601+1.4-12(2)2RTtest=311R

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: Nitrogen at 700 kPa pressure and 300K temperature enters a convergent divergent nozzle at negligible…

A:

Entropy

In physics, entropy means the amount of disorder or the degree of randomness associated with a thermodynamic system. The system is not self-organized when the entropy of the system is high. For instance, when a system is at an elevated temperature, its molecules are in random motion, vibrating and colliding with each other. During this scenario, the probability of finding a molecule at a particular place twice, is low. Under this circumstance, the system can be said to be in a high entropy.