Q3. A supersonic flow of air has a pressure of 1 x 10 N/m² and a temperature of 350 K. After expanding through a 35° tum, =? the Mach number is 3.5. Determine: · Angles 6,0, and 6,. Final flow properties p2 and Tz.

Q: Air with pressure, temperature and density corresponding to a standard sea level condition is…

A: Write the given values using suitable variables. Here P signifies second state pressure, and v…

Q: a) An aircraft is flying at a Mach number of 0.95 at an altitude where the pressure is 30kPa and the…

A:

Q: Q2: the static pressure to stagnation pressure ratio is 0.82. the stagnation temperature is 300k.…

A: Given data:

Q: A normoa shock wave exists in air flow with up stream M=2 and a pressure of 20kpa and temperature of…

A: Given: Upstressm properties: Mx=2Px=20kPaTx=15°C or 288K Solution: Downstream mach number is given…

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: Q3/ An air nozzle has an exit area 2 times the throat area. If a normal shock occurs at a plane…

A:

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

A:

Q: Q3. A supersonic flow of air has a pressure of 1 x 105 N/m2 and My a temperature of 350 K. After…

A: given data;⇒pressure(P)=1*105N/m2⇒temperature(T)=350K⇒mack number(M)=3.5

Q: Q/An airstream, at a temperature of 238 K, is moving at a speed of 773 m/s when it encounters an…

A: Temperature inlet = 238 K Velocity = 773 m/s Shock angle B1 = 38o

Q: Air flows subsonic in the duct, ignoring friction and heat of 984 kJ/kg. Pressure drop from p,= 220…

A: GIven DataP1=220kPaP2=116kPaT01=305Kq=984kJ/kg

Q: A normal shock wave exists in air flow with up stream M=2, and a pressure of 20 kpa and temperature…

A: M1=2  , and P1=20 kPa T1=15°C M1=V1γRT1V1=M1×γRT1V1=2×1.4×287×288V1=680.34 msec Now…

Q: 43. Determine the air temperature at first level for an airplane flies at two altitudes (µ2 = 43°,…

A: Given Data v1=740 m/s   Mach no difference = 0.3 μ2=43°

Q: 56. A supersonic aircraft flies with a velocity greater by 39 m-s1 at 7600 m elevation, (T = - 51 C°…

A:

Q: Find Mach number, total pressure loss, and entropy increase for the flow behind the shock wave when…

A: Given: The mach number before shock: M1 = 4

Q: impact tube

A: Given,  Static pressure=3psia or 20.6843kPa Total pressure=116kPa k=1.4 Temperature of…

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 village shaman is up to no good again. Having calibrated their pulley system, they now have a…

A: (a) Given data: Wind speed: 5 m/s Amount of potion: n = 104 moles Initial temperature: 20°C Final…

Q: Q4: : The pressure ratio across a normal shock wave that occurs in air is 1.4. A head of the shock…

A:

Q: For a moving normal shock wave the gas velocity represents the y-velocity when the normal shock wave…

A: For a moving normal shock wave the gas velocity represents the y-velocity when the normal shock wave…

Q: b) Air flowing at a velocity of '1039.6' km/hr has a static pressure of '83.17' kN/m2 and a…

A:

Q: 1. An air flow with a Mach number of 2.0 passes through an oblique shock wave inclined at an angle…

A: Solution   Calculate the deflection angle α          tanα=2tanθM2sin2θ-1M2γ+cos2θ+2

Q: Q1: Gas mixture flows isentropically from a reservoir where po = 700 KPa and T,= 305 k to a 150 mm…

A: Solved

Q: Q3: Supersonic divergent duct with Mach inlet 3 and exit Mach number equal to 0.4. Normal shock wave…

A: Given, Inlet Mach number, M1=3AiAi*=4.2346Outlet Mach number,M2=0.4AeAe*=1.5901AlsoAiAe=0.5 (Given…

Q: Q6:An air nozzle has an exit areal.8 times the throat area. If a normal shock occurs at a plane…

A: Given, Po=760KPa,To=350KAeAt=1.8AxAt=1.3considering specific heat ratio, y=1.4 Now, From gas…

Q: a-) Stop temperature at first point, stop pressure, stop density, Mach number, maximum speed and…

A: For solution refer below images.

Q: Q4:-A shock wave is moving down a constant area duct containing air. The air ahead of the shock wave…

A:

Q: The velocity ratio (v1/v2) of an isentropic flow through a supersonic wind tunnel is 0.615. if the…

A:

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: (Q) A converging-diverging nozzle discharges an over-expanded jet into a room. Calculate the…

A:

Q: the Figure (2), air flow in duct and heat is added between point 1 and point 2 by a rate of 420…

A: ⇒given data;⇒V1=100m/s⇒T1=500c       =50+273        =323K⇒P1=50KPa⇒heat added (Q)=420KJ/kg