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: Air at 7.20 MPa (abs.) and a temperature 1100K flows isentropically through a converging-diverging…

A: According to the given data as we know that  Po = 7.2Mpa  To =1100k  A*  = 0.01m2  for mach number 4…

Q: 5.) What is the Temperature in the Throat Section? * 354.851 О365.12 K O 378.35 K О398.88К

A: Given dataAt Throat section Mach Number = M = 1Speed of sound = a = 390 m/sWe have to find the…

Q: A normal shock produced by an explosion propagate at a constant velocity of 450 m/s into still air…

A:

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: Air enters a converging- diverging nozzle at a pressure of 830 kPa abs and a temperature of 32°C.…

A:

Q: flow by 15", as shown in the fīgure flow are 40 kPa and 263 K. respec

A:

Q: We are given the pressure on one side of a normal shock wave is 1 atmosphere, and the pressure and…

A: given Px = 1atm Py = 10 atm , Ty = 775K

Q: Can the Mach number of a fluid be greater than 1 after a normal shock wave? Explain.

A: Normal shock wave: The normal shock waves for supersonic flow are most likely to occurs in the…

Q: A flywheel weighted 1000 N is attached in the middle of the shaft and tensions of 300 N and 600 N…

A:

Q: 5. At 30000ft, estimate the magnitude of transonic drag rise. Using this estimate, calculate the…

A: Where terms followdM- magnitude of transonic drag riseM1- Mach numberMDD- Drag-divergence Mach…

Q: Shock waves are treated as discontinuities here, but theyactually have a very small fi nite…

A: The variation of the velocity, temperature, pressure and entropy of the before and after the shock…

Q: At a point in the flow over an F-15 high-performance fighter airplane, the density,temperature and…

A: Please go through the below answer. This is the second time I'm answering this questionExplanation:

Q: Race cars at the Indianapolis Speedway average speeds of185 mi/h. After determining the altitude of…

A: Given data Average speed of indianpolis is 185 miles per hour Attitude of indianpoils h = 218m Speed…

Q: It is required to expand 3 kg/s of air from stagnation conditions of 200kPa, 500K through a…

A: Giveen data It is required to expand 3 kg/s of air from stagnation conditions of 200kPa, 500K…

Q: A normal shock wave is positioned in a divergent portion where the cross-sectional area is 95cm of a…

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: 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: The Pitot tube on a supersonic aircraft (see the Video) cruising at an altitude of 25000 ft senses a…

A:

Q: In a convergent divergent passage normal shock wave forms in the divergent section. The Mach number…

A: Option (1)more than the mach number before the shock wave . Option (1) are correct, remaining are…

Q: At a section upstream of the throat of a converging-diverging nozzle, the air flow conditions are: T…

A:

Q: es with a speed of Two oblique sh window edges as and window edge eam the first shock per upstream…

A: Given: v1= 2750 km/hr= 763.89 m/s T1= 27 c= 300k P1=100 kpa Solution: M1= V1r×R T1      =…

Q: Given the conditions on a converging-diverging wind tunnel. At the reservoir pressure is measured to…

A:

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: Consider the following problem. We wish to design a convergent-divergentnozzle to expand a gas from…

A: A nozzle is a relatively simple device, just a specially shaped tube through which hot gases flow.…

Q: An explosion occurs which creates a plane normal shock wave propagating into a region of air that is…

A: Given:The stagnation pressure, Po = 1.0135 x 105 PaThe stagnation temperature, To = 290 KThe speed…

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: When a pitot-static tube is placed in a supersonic flow, the probe reads P = 190 kPa and P = 150…

A: Given data:To determine:Freestream mach number and velocityThe Mach number inside the shock can be…

Q: 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Just upstream of a shock wave, the air temperature and…

A: Given Data: Upstream temperature is T1 = 288 K. Upstream pressure is P1 = 1 atm. Downstream…

Q: 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow through a supersonic wind-tunnel…

A: Given Data Reservoir Properties  T0=500K    and P0=10atm Nozzle exit pressure P=1atm  Adiabatic…

Q: A uniform supersonic airstream travelling at a Mach number of 9.0 passes over a concave corner, as…

A: Mach number,M1=9.0shock angle,Assume,Deviation angle be

Q: Q6/ Air is he of heat transf velocity and Disregarding static pressur

A: Given data Amount of heat transfer = 60kJ/kg Velocity of air V2=620 m/sec static pressure P2=270 kPa…

Q: A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnation…

A: Given Data: M1 = 3.8 P = 5Mpa T = 1100K v2-v1 = 23o To find: 1) Downstream Mach 2) Downstream…

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

A: As per given question  Velocity =722.4 m/s Pressures = 1 atm Temperature =294.4 k We have to…

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.