Q2. Correct the false statement. 1) An oblique shock wave is always parallel to the incoming flow. 2) For Prandtl-Mever fan, an expansion wayes are Mach wayes
Q: (a.) A fluid at P1, V1, flows through a sudden 2:1 contraction, with Az/A1 = 1/2 (see figure below).…
A: given; A2/A1=12KL=0.25∆P=P2-P1
Q: An airplane uses a pitot-static tube as a velocimeter. Themeasurements, with their uncertainties,…
A: Given data: Static temperature, T = - 110C = 262 K Static pressure, P = 60 kPa Pressure difference ,…
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: 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: 6.7 A converging-diverging nozzle is designed to provide flow at Mach 2.0. With the nozzle…
A:
Q: Q3) A gas enters horizontal pipe with a 31O m/s. If the absolute pressure changes from 50 kpa to 80…
A: Given:Inlet velocity, V1=310 m/sinlet Pressure, P1=50 kPaoutlet Pressure, P2=80 kPaTemperature,…
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: A liquid of density ρ flows through the sudden contractionin Fig. P3.42 and exits to the atmosphere.…
A: Write the expression of the mass flow rate of the fluid. Write the continuity equation between…
Q: In Fig. P3.137 the piston drives water at 20 ° C. Neglectinglosses, estimate the exit velocity V 2…
A: At 20 degree celcius Density of water is 0.036055 lb/in3 Pressure at section 1 = Patm + Pressure due…
Q: In Fig. water exits from a nozzle into atmosphericpressure of 101 kPa. If the manometer fl uid has…
A: The value of pressure in section 1 can be calculated as, From the continuity equation,
Q: An airplane flies at two altitudes (v2 = 765 m-s, µ1 = 35°, the Mach no. ratio is 1.15), determine…
A:
Q: cross section S with velicity q1 and making an a
A: Liquid jet has cross-section area= S Velocity =q1 Angle =α
Q: Problem 4 A partly full water tank admits water at 85 N/s weight flow while ejecting water on the…
A:
Q: Air flows from a reservoir where p = 300 kPa and T = 500 K through a throat to in Fig. where there…
A:
Q: The orientation of a hole can make a difference. Considerholes A and B in Fig. which are identical…
A: Write the relation between pressures at entry and exit points of hole B and the Mach number of hole…
Q: propagates at à speed of normal shock wa m/s down a pipe thát is filled with hydrogen. The hydrogen…
A:
Q: c) Prove mathematically that shock wave cannot occur in subsonic flow
A: Solution: Change in entropy across shock is given by, ∆sR=γγ-1ln2(γ+1)M2+γ-1γ+1+1γ-1ln2γγ+1M2-γ-1γ+1…
Q: 72. In an airplane engine (Fth = 33.2 kN, p, = 1.34 P2, P2 = 99.5 kPa, T2 = 235 °C, v, = 105 m-s“,…
A: Write the given values along with the suitable variables.
Q: 74. Find the ratio of Mach no.s of an aircraft flies with a velocity greater by 39 m-s1 at 8000 m…
A: As given that At elevation 8000m and temperature is T=-41 °C =232 ;At this temperature velocity of…
Q: ir, supplied by a reservoir at 450 kPa, flows through a con verging-diverging nozzle whose throat…
A:
Q: Carbon dioxide convergent-divergent to a Lule of 60 m / s, 310 °C and 300 kPa in its case, it enters…
A: Nozzle: Nozzle is a device which having varying in cross section, in which pressure is reduced by…
Q: In Fig. P3.131 both fluids are at 20°C. If V, = 1.7 ft/s and losses are neglected, what should the…
A:
Q: A a5 mm. fire hose dischargos water through a nozzle having a jet diametor of 25 mm. The head last…
A:
Q: Methane is flowing through an insulated 15-cm diameter pipe. The entering conditions are kPa, 100°C,…
A: Given data,d=15cmf=0.023P1=600kpaT1=100°Cm=5kgs
Q: Q5. A duct of a friction length of fx/D = 124 is connected to a Duct reservoir. A nozzle is attached…
A: Given: Receiver pressure, Pe=103.4 kPafLD=12.4Nozzle exit area, Ae=6 cm2Nozzle inlet area, A3=9…
Q: An 8-in model pump delivering 180°F water at 800 gal/minand 2400 r/min begins to cavitate when the…
A: At 180 degrees Fahrenheit, the properties of water are: The pressure of the model pump is 1600…
Q: Q2: Helium, at To = 400 K, enters a nozzle isentropically. At section 1, where A1 = 0.1 m2, a…
A:
Q: Suppose a gas flows through a constant insulated path. Parameters of temperature, pressure and mach…
A: given; ⇒initial temperature(T0)=520R⇒initial pressure(P0)=50psi⇒mack number (M0)=0.45⇒at…
Q: 58. Find the height of a supersonic airplane (v = 670 m-s1, T = - 44 C°) when the time between…
A: Given data:- Temperature, T=-44°C=-44+273=229K characteristic gas constant, R=287Jkg-K For air,…
Q: Differentiate between impulse and reaction turbines?
A: To find : Differentiate between impulse and reaction turbines
Q: what will be the pressure gradient (kpa/m) at L=D30 cm through the nozzle? At L=0, the liquid flows…
A:
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: 72. In an airplane engine (Fth = 33.2 kN, p, = 1.34 P2, P2 = 99.5 kPa, T2 = 235 °C, v, = 105 m-s“,…
A:
Q: In Fig. P3.60 the jet strikes a vane that moves to the right at constant velocity Ve on a…
A: The free body diagram of forces acting on the vane is shown below. The initial relative…
Q: Gas turbine engine (T2 = 214 °C, v2 = 764 m-s“, A2 = 0.63 m?, Fth = 32.8 kN, A, = 3 A2, p1 = 1.17…
A: Solution First Calculate the mass flow rate m=ρ2A2v2=ρ11.170.63×764=411.38ρ1
Q: Q2: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation…
A: Given data: - The throat area of the nozzle is A = 7 cm2. The stagnation pressure is Po = 130 kPa.…
Q: Q2: Air flows out of a nozzle straight up 30 m. What is nozzle velocity exit?
A: Given data : Acceleration due to gravity=g Height from nozzle=h To find : Velocity exit
Q: Mention some engineering applications that use the impact of jet theory
A: Given data Engineering applications of impact of jet theory
Q: The velocity monitoring of a fluid is u = 48xy v = N. (48 + x2 + y2) Find the current function. Is…
A: Given: u = 48*xy v= N[48 + x2+y2 ] Let the current or stream function be psi We have u =…
Q: Consider a plane Couette flow of a viscous fluid confined between two flat plates at a distance b…
A: Since we only answer up to three subparts, we will answer the first three. Please resubmit the…
Q: Consider a following figure showing a jet of water supporting a weight of 100 N at a heigh of 5m.…
A: Given Weight = 100N Height = 5 m Exit velocity = 20 m/s To find Diameter of the nozzle A jet of…
Q: 60. Find the Mach no. of an aircraft flies with the same Mach no. at elevations of 8600m (T =- 54…
A: Now as we haveMa=VCHer C=γRTγair=1.4R=287 J/kgKT=-61°C=273-61=212KC=1.4×287×212C=291.8
Q: The converging-diverging nozzle shown in Fig. P3.22 expands and accelerates dry air to supersonic…
A:
Q: The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic…
A: Inlet Area, A1=π0.0124 Outlet Area, A2=π(0.025)24 P1=284000Pa T1=665K P2=8000Pa T2=240K V1=517m/s
Q: Air enters a nozzle at 2.21 m3 kg and 30m/s. How much mass is entering the system if the orifice is…
A:
Q: Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 60.0…
A:
Q: (b) A normal shock wave passes through stagnant air at 22°C and atmospheric pressure of 130 kPa with…
A:
Q: You wish to water your garden with 100 ft of 5/8-in-diameterhose whose roughness is 0.011 in. What…
A: Given Data Diameter of the pipe is: d=58 in Length of the pipe is: L=100 ft Gauge pressure at the…
Q: essure in Denver, locity of 9 m/s over ate if the air flows
A:
Q: Q1) Air flows over a plane wall at a Mach number 3.5, the pressure in the flow being 100kpa. The…
A: To find: The turning angle of corner. Given: The Mach number at plane wall is M1=3.5. The pressure…
Step by step
Solved in 2 steps
- c) Prove mathematically that shock wave cannot occur in subsonic flowThe village shaman is up to no good again. Having calibrated their pulley system, they now have a constant source of perfect liquid (cp,l = 5R) potion at T = 20.0°C. They would now like disperse the potion amongst the villagers for some likely nefarious purpose... They decide to convert it to a vapor (Cp,v 15R) and let it then become an aerosol, which the villagers will inhale unsuspect- ingly. The potion is known to vaporize at 70°C with an enthalpy of vaporization Ahvap = 25 kJ/mol. =Q2: A/ Air is flowing in a convergent nozzle. The stagnation pressure is 350 KPa, the stagnation temperature is 400 K and Mach number is 0.7. If the cross sectional area at this location is 10 x 10-3 m2 , find 1) The static temperature and static pressure 2) The velocity at this location. 3) The area and static temperature and static pressure at the exit where Mach number =1 4) The mas flow rate of nozzle
- Air flows isentropically through a channel. From two points inside this channel 1st speed 240 m / s, temperature 320 K and pressure 170 kPa. At the 2nd point, the speed is 290 m / s and the pressure is 135 kPa. a-) Stop temperature at first point, stop pressure, stop density, Mach number, maximum speed and critical point speed b-) find the stopping pressure of the second point.1. A normal shock wave with a velocity of 700 m/s moves down a tube into air with static properties of 40 kPa and 320 K. At the end of the tube, a piston is moving at 60 m/s, as shown below. Find the velocity of the reflected wave and the static and stagnation pressures (relative to the tube) behind the reflected wave. Vw= 700 m/s V = 60 m/s P = 40 kPa T= 320 KQ1) Air flows over a plane wall at a Mach number 3.5, the pressure in the flow being 100kpa. The wall turns through an the pressure downstream of the that angle leading to generation of an oblique shock wave whose strength is such corner is 548kpa. Find the turning angle of corner.
- 2. Find the ratio of Mach no.s of an aircraft flies with a velocity greater by 39 m-s1 at 6000 m elevation, (T =- 43 C° at 6000 m) and (T =- 54 C° at 7000 m, M = 1.8). ju> lw daQ4. M 1) The flow around a comer makes the edges of the expansion fan indicated by the angles as shown. 6,=142.7 (a) Determine the Mach number before and after the corner. 8= 19.20 (b) Through what angle was the flow turned, and what is the angle of the expansion fan (6,)? Figure Q4,1)The mass flow rate of a calorically perfect gas (C₁ = constant) through a Convergent-Divergent nozzle is given by, m = A Pt VT₁ M (1+ y +1 YM²) 2(3-1) (a) Derive the above relation from fundamental principals. Here, P₁, is total (or Stagnation) pressure and T₁ is total temperature, M is Mach number, A is local area of nozzle. (b) Prove mathematically that the maximum airflow limit occurs when the Mach number is equal to one and obtain below relation. m A Pt √√Tt Note: The limiting of the maximum mass flow rate when M =1, is called choking of the flow or Choked flow. Hint: https://www.grc.nasa.gov/www/k-12/rocket/mflchk.html y+1 2(y-1) √(4¹) R
- 3. In a steady flow open system, a fluid moves between two boundaries. In boundary 1: A: = 0.028 m?, V1 = 32.5 m/min, vị = 0.025 m²/kg, and P1 = 300 kPaa. In boundary 2: A2 = 0.056 m?, density = 3.2 kg/m?, and P2 = 100 kPaa. Determine a) the mass flow rate; b) the velocity in boundary 2; c) the change of kinetic energy between boundaries; and d) the change in flow energy between boundaries.Where necessary, assume air as an ideal gas and consider R = 287J/(kg.K), Cp = 1005 J/(kg.K), Cv = 718 J/(kg.K). A nozzle is a device that is used to increase the velocity of a fluidby varying the cross-sectional area. At the last section of a jetengine (Fig Q1.a, section 5), air with a mass flow rate of 50 kg/s ata pressure of 500 kPa and a temperature of 600 K enters a nozzlewith an inlet cross-sectional area of 5 m2. The exit area of thenozzle is 20% of its inlet area. The air leaves the nozzle at avelocity of 300 m/s. The nozzle is not well-insulated and duringthis process, 5 kJ/kg heat is lost. (iv) Determine the temperature of the air as it leaves the nozzle.(v) Calculate the pressure of the air as it leaves the nozzle.52. Calculate the air temperature at first level for an airplane flies at two altitudes (v1 = 745 m-s, µ2 =D33°, the Mach no. difference is 0.24).