Maz, P2 Maj = 3 P, = 100 kPa 50

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

A:

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: A projectile travels at a speed of 260 m/s in air where the temperature is -10 °C. Find the Mach…

A: Mach number is defined as the ratio of inertia force to the surface tension force. It is mostly used…

Q: Prablen (t A large VacuuM tank, hetdat 6okAt abslute, Sucke searlevel standard qir throngh f…

A:

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: 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: 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: Calculate : 1. Upstream velocity Vi and deflection angle 0. 2. Downstream Mach number M2

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Q: Q5: air velocity decrease from 480m/s chrough the shock. If the pressure and density upstream of the…

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Q: Figure  shows the exit of a converging–diverging nozzle,where an oblique shock pattern is formed. In…

A: Hello. Since your question has multiple sub-parts, we will solve the first three sub-parts for you.…

Q: 6.7 A converging-diverging nozzle is designed to provide flow at Mach 2.0. With the nozzle…

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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 pitot tube, mounted on an airplane fl ying at 8000 m standardaltitude, reads a stagnation pressure…

A: Solution : First, we calculate the Mach number by using the following equation

Q: A normal shock wave with a velocity of 700 m/s moves down a tube into air with static properties of…

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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: -Converging nozzle is supplied with Po=10 bars and To=1000 K and discharges to atmosphere with…

A: Given: Stagnation Pressure P0=10barsStagnation Temperature T0=1000KExit pressure P=9.8bars…

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: impact tube

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

Q: The supersonic nozzle of Fig. P9.138 is overexpanded (case G of Fig. 9.12) with Ae/At= 3.0 and a…

A: Area ratio = 3 Stagnation pressure = 350 KPa Angle = 4o

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

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Q: The pressure ratio across a normal shock wave that occurs in air is 1.25. Ahead of the shock wave,…

A: Given:Pressure , P2=100temperature, T2=15o C=15+273T2=288 K

Q: Air enters a duct with constant area at the pressure of 139 kPa, temperature of 293 K, and velocity…

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Q: What is the atmospheric pressure? kPa Required informetion Ar in a tank at 120 kPa and 300 K…

A:

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: 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: 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: Q5: A supersonic projectile pushing gas ahead in tube filled with initially still air at 294K and…

A: Given: upstream pressure = 101.3 kPa upstream temperature = 294 K downstream pressure = 608 kPa

Q: 30. A normal shock wave across which the pressure ratio is 1.25 is propagating down a duct…

A: Given dataPrssure ratio P2P1 = 1.25P1 = 120kPaT1 = 350CTo determine the pressure and temperature…

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: If there are no shock waves and the pressure at one ductsection in Fig.  is 55.5 kPa, what is the…

A: given data as per the question The temperature of tank =400 k The pressure of tank =300 Kpa…

Q: 5 Consider the subsonic flow through a divergent duct with area ratio A2/A, 1.7. If the inlet…

A:

Q: An airplane is flying at 1500m witha speed of 45 m/s. What is the stagnation pressure measured in…

A: Write down the given value using suitable variables. Here H1 signifies the initial height of the…

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: Problem (1): A large vacuum tank, held at sokf -absolute. Suck, sea-level standard air through a…

A: Given Data The pressure inside the tank is: P2=60 kPa The nozzle throat diameter is: d=3 cm=0.03 m…

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; 1 23 kg/m'…

A: Data given-  M1 = 3  P1 = 1 atm  ρ = 1.23 kg/m3  Need to calculate the downstream values

Q: Air flows through a converging–diverging nozzle betweentwo large reservoirs, as shown in Fig.  A…

A: Given Data: The reading of manometer is, h=15 cm. The pressure at the nozzle inlet is, P0=300 kPa.…

Q: Air flows isentropically through a variable-area duct. Atsection 1, A1= 20 cm2, p1= 300 kPa, ρ1=…

A: If the areas are the same but the velocities are different, there must be a sonic throat in between:…

Q: A converging–diverging nozzle exits smoothly to sealevelstandard atmosphere. It is supplied by a…

A: Given:Volume of tank,V=40m3Initial pressure of tank,Pi=800KPaInitial temperature of…

Q: . An air tank with a nozzle has a pressure of 196.32 KPa and density of 1.9 Kg/m3. Outsic diverging…

A: P=196.32kPa=196320Paρ=1.9kg/m3Mach no throat and exit= 1 and 1.5A=0.11m2 To-Find 1) Temperature and…

Q: Air flows through a constant cross-section conduit with Mack number Ma = 1 at 200 KPa pressure and…

A: given; mach number(Ma)=1initial pressure(P)=200KPainitial temperature(T1)=1000c(a)stagnation…

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…