The stagnation chamber of a wind tunnel is connected to a high-pressure air bottle farm which is outside the laboratory building. The two are connected by a long pipe of 4-in inside diameter. If the static pressure ratio between the bottle farm and the stagnation chamber is 10, and the bottle-farm static pressure is 100 atm, how long can the pipe be without choking? Assumeadiabatic, subsonic, one-dimensional flow

Q: A constant area adiabatic wind tunnel is to be designed to provide a test section of air flowing at…

A: Given Data The mach number is: M=3 The pressure is: 7 kPa The temperature is: 255 K The stagnation…

Q: (0 The flow in a hard-disk drive at P=1 atm & T=25 C. (i) Flow over airfoils (i) Supersonic flight…

A: given; which process in continuum process.

Q: An airfoil section is being tested in a wind tunnel. The freestream properties are: velocity = 160…

A:

Q: Now suppose that your supersonic vehicle is cruising at a velocity of 2178 m/s and the estimated…

A: Step 1:Step 2:Step 3:Step 4:

Q: Assume a design of a Mach 6.5 hypersonic wind tunnel using air as the test medium. We want the…

A: Given data: - The Mach number is M = 6.5. The standard altitude is H = 55 km.

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

A:

Q: Consider a slender body of revolution at zero angle of attack in supersonic flow with M.. = 3.0 as…

A:

Q: In a convergent nozzle the flow conditions are subsonic. As the flow progresses the velocity of…

A:

Q: 1. A two dimensional supersonic airfoil has the cross-section shown below (base: 2.8 m, base angles…

A: Given   Mach number, M = 2.4             Pressure, P = 25 kPa                  Base, w = 2.8 m…

Q: An unconfined supersonic flow passes over the contoured wall shown below. The wall segment AB is a…

A: Given:To Find:Wall static pressures at B and C.

Q: A supersonic inlet is sketched below and contains an oblique shock wave followed by a normal shock…

A: Given:M1=3T1=300 KP1=101.3 KPa

Q: 1- Calculate the pressure, temperature and velocity prior to the shock wave. 2- Determine if the…

A:

Q: An airfoil is being tested in a low-speed subsonic wind tunnel. The velocity of the flow in the test…

A: Given question is related to fluid mechanics.   Given data: Velocity of flow = v = 81 ft/s…

Q: Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air…

A: To calculate the mass flow rate of air through the nozzle, we can use the continuity equation, which…

Q: Air at V_1 = 800 m/s, p_1 = 100 kPa, and T_1 = 300 K passes through a normal shock. Calculate the…

A: Dear Students

Q: Air, assumed to be an ideal gas with k = 1.40, fl ows isentropicallythrough a nozzle. At section 1,…

A: Given data: The temperature at the section 2 is, T2 = -50 0 The ratio of specific heat is, k =…

Q: An experimental airfoil was studied using the open-circuit subsonic wind tunnel of Philippine State…

A: An experimental airfoil was studied using the open-circuit subsonic wind tunnel of Philippine State…

Q: Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area A1 = 2 m2…

A: Given:A1=2 m2A2=0.5 m2P2=1 atm =101.325 KPaV2=40 m/s

Q: Reservoir Pressure in psf A B Reservoir Temperature in degrees Rankine Throat Area in square foot

A:

Q: The scramjet of Fig.  operates with supersonic fl owthroughout. Assume that the heat addition of 500…

A: Given that, Heat addition between section 2 and 3, Q=500 kJ/kgArea between section 2 & 3, A=0.2…

Q: (b) Show that shock happens for a compressible flow only at supersonic flow

A: According to terms and conditions of   bartleby we can only provide a) solution . Althrough you have…

Q: Consider a business jet, like the Gulfstream G550, flying at a standard altitude of 30,000 f and V1…

A: Given:Standard altitude, h=30000 ft or 9144 mvelocity of stream, V1=525 mph or 145.833 m/s

Q: Air enters a pipe of 1in diameter at subsonic velocity and P: 30 psia, T-550 "R. If the pipe is 10ft…

A: Given: d=1 inP1=30 psiaT1=550 RL=10 ftf=0.025P2=20 psiaγair=1.4 To find: Mass flow Mach number at…

Q: Q1// Air stream flow in a convergent- divergent nozzle, with a stagnation pressure of 120 kPa, the…

A: The nozzle is both convergent and divergent. The forward section of the nozzle is convergent,…

Q: M = 3.0 60 A = 40° ة و 6 = 20°

A:

Q: An airfoil is in a freestream where Poo = 0.8bar, p=0.93 kg/m³ and Voo=412m/s At a point on the…

A: Given:  P∞= 0.8 barρ∞=0.93 kg/m3V∞= 412  m/s P= 0.625 bar

Q: Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area of 2 m2 and…

A: Given: A1=2m^3, A2=.5m^3, P2= 1atm, V2=40m/s.  With the help of continuity equation and Bernoulli…

Q: y = 1.4 M = 3.0 % $ = 40° 0 ts=20°

A:

Q: An aircraft where the ambient parameters are density = 0.785 kg/m^3, p= 0.50 atm, and velocity = 350…

A: Given: Let us consider the given data, Stream Pressure, p=0.50 atm Stream density, ρ=0.785 kgm3…

Q: Example 2 Which of the two aircrafts in the figure flies at a supersonic speed? Air 220 K V = 320…

A: According to the information given, both airplanes are traveling at the same speed of 320 m/s. The…

Q: mounted in the test-section of a subsonic wind tunnel at standard sea level condition. The velocity…

A:

Q: In a convergent nozzle the flow conditions are supersonic. As the flow progresses the velocity of…

A: condition : convergent nozzle super sonic flow