Derive the following equation and draw the shape of nozzle and diffuser for subsonic, sonic and dA de (1-M) supersonic flow. %3D A pc
Q: |The pressure ratio across a normal shock wave that occurs in air is 1.4. A head of the shock is…
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Q: Air discharge through a nozzle. A normal shock wave occurs at section of the flow at which the Mach…
A: Given Data At the inlet Ma1=2.5 P1=40KPa T1=-20C=253K For air Y=1.4
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: JI Air stream flow in a convergent - divergent nozzle, with a stagnation pressure of 120 kPa, the…
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Q: A Perfect gas (assumed to be air) is a supplied to a Converging Nozzle at low Velocity at at /copsig…
A: Given Data The inlet pressure is: P1=100 psia=689.476 kPa The exit pressure is: P2=Patm=101.325 kPa…
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Q: When the reservoir pressure and temperature of a supersonic wind tunnel are 15 atm and 750 K,…
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Q: 91. 6.13. Air enters a device with a Mach number of Mi 2.0 and leaves with M2 = 0.25. The ratio of…
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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…
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Q: -Converging nozzle is supplied with Po=10 bars and To=1000 K and discharges to atmosphere with…
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A: solved
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Q: Example 11.2 An airstream, at a temperature of 238 K, is moving at a speed of 773 m s when it…
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A: GivenT1=300oC=573KP=1atm=101.325KPaVair=0.9×Vsoundγ=1.4
Q: a Mach number of 0.7 in air at with a static pressure of 101 kPa. Calc produced by this aircraft.…
A: Handwritten.jpg
Q: 78. 5.23. Assume that a supersonic nozzle operating isentropically delivers air at an exit Mach…
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Q: Help me solve this problem A uniform air stream of Ma corner as shown in figure. T stream are 223 K…
A: as per our guidelines i solved 1st 3 questions
Q: he inlet Mach number is 3.2 and the outlet Mach number is 23, then the area is divergent lect one
A: Ans: The given statement is true.
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A: given data;initial temperature (T1)=2900c=290+273=563Kpressure (P1)=105Patemperature at downstream…
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Q: QI. Air flows through a constant cross-section conduit with Mack number Ma = 1 at 200 KPa pressure…
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A: Assumption 1) Non-Viscous 2) Adiabatic 3) Isentropic 4) Steady flow
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Q: Air flows isentropically through a duct shown in Figure 3. Subsonic Possibly supersonic Throat P s00…
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- One type of supersonic wind tunnel is a blow-down tunnel, where air is stored in a high-pressure reservoir, and then, upon the opening of a valve, exhausted through the tunnel into a vacuum tank or simply into the open atmosphere at the downstream end of the tunnel. For this example, weconsider just the high-pressure reservoir as a storage tank that is being charged with air by a high-pressure pump. As air is being pumped into the constant-volume reservoir, the air pressure inside the reservoir increases. The pump continues to charge the reservoir until the desired pressure is achieved.Consider a reservoir with an internal volume of 30 m3. As air is pumped into the reservoir, the air pressure inside the reservoir continually increases with time. Consider the instant during the charging process when the reservoir pressure is 10 atm. Assume the air temperature inside the reservoir is held constant at 300 K by means of a heat exchanger.Air is pumped into the reservoir at the rate of 1…A normoa shock wave exists in air flow with up stream M=2 and a pressure of 20kpa and temperature of 15 c find the Mach number pressure stagntion pressure temperature stagntion temperature and air velocity down stream of the shock WaveFor a hotshot wind tunnel with T=50o0k and P=100 MPa. Calculate and plot Mach number as a function of ratio A/At for the choked nozzle of the tunnel for 1) air in thermochemical equilibrium and 2) air with chemical composition and all internal energies except for translational.
- he reservoir pressure and temperature for a Laval nozzle are 5 atm [abs] and 520 K,respectively. The flow is isentropically expanded to supersonic speed at the nozzle exitwith area Ae = 4in2. If the exit-to-throat area ratio is 2.295, calculate the followingexit properties: d) ρe; e) p0,e; f) T0,e; gamma = 1.4, R = 287 Please show all work!!Example 3 Helium expands in a nozzle at from 1.2 MPa, 600 K and negligible velocity to 0.1 MPa. Khelium = 1.6 and Cp Calculate the throat and exit areas for a mass flow rate of 0.1 kg/s, assuming the nozzle (a) is isentropic and Why must this nozzle be converging-diverging nozzle?Supersonic airflow takes a 5° expansion turn, as inFig. Compute the downstream Mach number andpressure, and compare with small-disturbance theory.
- 60. Find the Mach no. of an aircraft flies with the same Mach no. at elevations of 8600m (T =- 54 C°) and 11600 m (T = – 61 C°), if the aircraft flies 10% slower at 11600 m altitude. Joli s dasExample 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848For Air Assume: y =1.4 and R = 287 J/kg K Question B1 a) Air is flowing at a Mach number of 0.6 in a two-dimensional duct at a location where the area is of 0.75 m². At this location the static pressure is 50 kPa and the static temperature is 300 K. 1- Calculate the mass flow rate through the duct; [2 marks] 2- What percentage in area change would be necessary to reach a Mach number of 0.75? [2 marks] 3- What percentage in area change would be necessary to reach a Mach number of 1.00? [2 marks] b) A normal shock wave occurs in a gas with an unknown specific heat ratio. The static pressure ratio across the normal shock wave is 10.6. The Mach number downstream of the shock wave is equal to 0.495, find the specific heat ratio of the gas and the velocity ratio across the shock wave. [8 marks] c) Explain why successive infinitesimal compression waves tend to reinforce and form a shock wave. Use sketches to illustrate your answer. [5 marks] d) Show that for a choked convergent nozzle further…
- Compute stagnation enthalpy of air at normal conditions (P=1atm, T=300K) moving with velocity of 1398 m/s. What temperature of air we will observe?Design the 2D steady MOC contour for a super sonic nozzle assuming that the expansion section is a simple corner of some fixed angle, with the straightening section being designed to produce uniform outflow. The inflow for your nozzle is to be M = 1, gamma = 1.4, P = 101325, T = 300K, incoming flow area of 1m, with 1m depth into the page. The exit Mach number of your design is to be M = 3. Note to execute this properly you will need to compute v (nu) as a function of M, and viceversa. Please use Matlab for results.A typical carbon dioxide tank for a paintball gun holdsabout 12 oz of liquid CO2. The tank is fi lled no more thanone-third with liquid, which, at room temperature, maintainsthe gaseous phase at about 850 psia. (a) If a valve isopened that simulates a converging nozzle with an exitdiameter of 0.050 in, what mass fl ow and exit velocityresults? (b) Repeat the calculations for helium.