430 K 50° Shock waves

Q: Engineers call the supersonic combustion in a scramjetengine almost miraculous, “like lighting a…

A: Given Data: The area at section 1 and 4 is: A1=1 m2. The area at section 2 and 4 is: A2=0.2 m2. The…

Q: uniform supersonic flow of a perfect gas with y = 1.4, a Mach number of 3.0, and an up- eam static…

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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: We wish to design a supersonic wind tunnel that produces a Mach 2.8flow at standard sea level…

A: Given Data: The exit Mach is: Me = 2.8 The mass flow rate of air is: 1 slugs/s The expression to…

Q: Consider a flat plate at α = 20◦ in a Mach 20 freestream. Using straightnewtonian theory, calculate…

A: Given data

Q: Downstream of a normal shock wave, in airflow, the conditionsare T2 = 603 K, V2= 222 m/s, and p2 =…

A: Given that, Mach Number at state 2 will be calculated as follows,

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: JI Air stream flow in a convergent - divergent nozzle, with a stagnation pressure of 120 kPa, the…

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Q: Consider the Gulfstream IV flying at Mach = 0.8 at an altitude with atmospheric pressure of…

A: Given data Mach number of aircraft = 0.8 Weight = 73000 lb S = 950 ft2 AR = 5.92 CD,0 = 0.015 K =…

Q: Consider a diamond-shaped airfoil. The maximum thickness is 0.04 and occurs at mid-chord. The…

A: Given data- 1. a diamond shaped airfoil 2. Thickness of the foil=0.04m 3. Mach number =2.0 4.Angle…

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M 3; 1 atm, and p, = 1…

A: Given: Normal shock wave in air. The upstream condition are: M1=3P1=1 atmρ=1.23 kg/m3

Q: A high-pressure air reservoir is connected to the inlet of a convergent-divergent nozzle with an…

A: Nozzle : It is a device which having reducing cross sectional area  from entrance to exit.  This…

Q: A projectile travelling at supersonic speed produces a Mach cone angle of 30 b) degree. Calculate…

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Q: A large tank at 500 K and 165 kPa feeds air to a convergingnozzle. The back pressure outside the…

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Q: Using shock-expansion theory, calculate the lift and drag coefficients for a flat plate at a 5°…

A: Upper pressure ratio is calculated using P-M expansion theory. Lower pressure ratio is calculated…

Q: Compressible laminar fl ow, f≈ 64/Re, may occur in capillarytubes. Consider air, at stagnation…

A: Given data: *The stagnation temperature of the air is T=100°C. *The stagnation pressure of the air…

Q: Supersonic air takes a 5° compression turn, as inFig. . Compute the downstream pressure and…

A: Write the given information.

Q: Consider an oblique shock wave with a wave angle of 36.87◦. Theupstream flow is given by M1 = 3 and…

A: Given data Oblique shock wave with a wave angle of 36.870  Upstream flow of mach with Mach no M1 = 3…

Q: Consider a normal shock wave in air The upstream conditions are given by M = 3; 1 atm, and p1 M2,…

A: From the given data: p1=1 atm = 101.32 kPaInitial temperature is given…

Q: a) A convergent nozzle with a given area ratio is supplied with air at a constant stagnation…

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Q: An airflow at Mach 0.6 passes through a channel with a cross-sectional area of 50 cm?. The static…

A: Please find the solution below

Q: The reservoir pressure and temperature for a convergent-divergent nozzleare 5 atm and 520◦R,…

A: From the Isentropic flow properties table, At, Ae / A* = 2.193: Me = 2.3 P0ePe=12.5T0eTe=2.058 For…

Q: Air at 20°C and 1 atm flow past a long flat plate, at the endof which is placed a narrow scoop, as…

A: Write the properties of air at a given temperature value. Determine the Reynold number for the…

Q: Consider a diamond-wedge airfoil such as shown , with ahalf-angle ε = 10◦. The airfoil is at an…

A:

Q: 1. A flat plate airfoil with a chord length of 1 m and a width of 6 m is required to generate a lift…

A: Given , chord length (C) - 1m Width(L) - 6m lift force (FL) -40,000 N mach number (M) - 2…

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: Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of…

A: Given data Mach number = 0.35 Altitude = 30000 ft Weight = 73000 lb S = 950 ft2 AR = 5.92  CD,0 =…

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, at stagnation conditions of 450 K and 250 kPa, fl owsthrough a nozzle. At section 1, where the…

A: Given data To determine the Mach number and the stagnation pressure just downstream of the shock.

Q: An isentropic converging-diverging nozzle receives air from a huge reservoir where the temperature…

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Q: Air enters a pipe of 1-cm diameter and 1.2-m length at p1 = 220 kPa and T1 = 300 K. If f = 0.025 and…

A: Given data: The area of the flow is

Q: An isentropic converging-diverging nozzle feeds an insulated constant area duct, as shown in the…

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Q: Air, from a reservoir at 350 K and 500 kPa, fl ows througha converging–diverging nozzle. The throat…

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Q: Q4. ajExplane the magnus effect in the potential fow b) A cylinder woith 50 cm in length, is under…

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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: An experimental scramjet aircraft is flying at an altitude of 25,000m at Mach 5. Considering it;s…

A: Given: M1 =5  delta = 5 deg P2/P1 = ?

Q: A converging–diverging nozzle with a 4:1 exit-area ratioand p0 = 500 kPa operates in an…

A: Given data: The stagnation pressure is Po = 500 kPa. The receiver pressure is Pa = 10 kPa. The…

Q: Air flows from a tank through a nozzle into the standardatmosphere, as in Fig.  A normal shock…

A: Given data as per the question Area of throat =10 cm2 Area at exit =14 cm2 The temperature of air…

Q: A perfect gas (y = 1.4) enters a converging-diverging nozzle with a Mách number of 0.50 and local…

A: gama =1.4 inlet mach number (M1) =0.5 Inlet velocity (V1) = 165 m/s  P1 =280 KPa T1 = 280 K Throat…

Q: Air enters a circular variable area converging duct at a temperature of 500 K and the static…

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Q: When an oblique shock strikes a solid wall, it reflects as ashock of sufficient strength to cause…

A: Given, Ma1 = 2.5 β1 = 40o p1 = 100 kPa

Q: A converging-diverging nozzle has a throat area of 10 cm2and an exit area of 28.96 cm2. A normal…

A: giventhroat area a=10 cm2exit area A= 28.96 cm2upstream tank temperature T= 400 Knormal shock stands…

Q: Consider a flat plate at an angle of attack α to a Mach 2.4 airflow at 1 atmpressure. What is the…

A: M1=2.4P1=1 atm

Q: A large reservoir at 20 °C and 800 kPa is used to fill a smallinsulated tank through a…

A: Given: throat area = 1 cm2 exit area = 1.66 cm2 volume= 1 m3 To determine: (a) Elapsed time when…