e Tr1 = 650°R and q* = 500 BTU/lbm, respectively. Calculate a) the inlet Mach number Mị b) exit total temperature T2 Cp = 0.24 BTUMbm°R, y = 1.4
Q: Calculate the ratio of kinetic energy to internal energy at a point in an airflow where the Mach…
A: We know that Mach number is the ratio of the velocity of the fluid to the velocity of sound in the…
Q: the flow phenomenon across a convergent and divergent nozzle when the p the stagnation pressure at…
A: Function of Nozzle A nozzle is a fluid-accelerating device. The velocity of the fluid increases as…
Q: 6.33 A normal-shock inlet operates in a Mach 1.86 stream with ambient static pressure of Po = 30…
A: GIVEN:- M=1.86 P0=30KPA
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: Q2: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit…
A:
Q: Prablen (t A large VacuuM tank, hetdat 6okAt abslute, Sucke searlevel standard qir throngh f…
A:
Q: The upstream flow properties are T1= 280 K and V= 2000 mph. What is downstream Mach number?
A: The Mach number, M, is defined as the ratio of the actual velocity V to the sonic velocity c, M=Vc…
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: Q2: the static pressure to stagnation pressure ratio is 0.82. the stagnation temperature is 300k.…
A: Given data:
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: 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: 52. Calculate the air temperature at first level for an airplane flies at two altitudes (v, = 745…
A: Given: v1=745 m/sμ2=33°∆M=0.24
Q: Q.5. With careful design, one can orient the bend on the lower wall so that the reflected wave is…
A: Please find the solution below
Q: 2019 \ 2020 static pressure in the air stream is 50kpa, static temperature is 298K. Calculate Answer…
A: Mach no is a property of the fluid that represents the ratio of flow velocity across a boundary to…
Q: The large compressed - air tank shown in the figure bellow exhausts from a nozzle at an exit…
A:
Q: Determine the ini tial Mach number, exit pressure ,exit temperature and stagnation pressure loss if…
A:
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: Supersonic air takes a 5° compression turn, as inFig. . Compute the downstream pressure and…
A: Write the given information.
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: When operating at design conditions (smooth exit to sealevelpressure), a rocket engine has a thrust…
A: Write the given data.
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: 45. 4.7. The temperature of argon is 100 F, the pressure 42 psia, and the velocity 2264 ft/ sec.…
A:
Q: The static pressure to stagnation pressure ratio at a point in a gas flow field is measured with a…
A: From the data given in question, Ratio of specific heat for air = γ = 1.4
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: 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: The SR-71 Blackbird is the fastest production plane capable of reaching speeds of more than Mach 3,…
A: GivenMach no. for blackbird M=3specific heat of air R=287j/kg.kspecific heat ratio γ=1.4To…
Q: diheoat = 8 cm 1 2 Exit Po da = 18 cm Shock wave Figure 4 [Gambarajah 4] (i) Determine the Mach…
A: The nozzle is a device that has varying cross-sections, in which pressure is reduced by expansion…
Q: For a moving normal shock wave the gas velocity represents the y-velocity when the normal shock wave…
A: For a moving normal shock wave the gas velocity represents the y-velocity when the normal shock wave…
Q: 13.8 (a) Describe briefly the various losses occurring in an inward- flow radial turbine stage. (b)…
A: The radial flow turbine is defined as the turbine in which flow enters radially. The main difference…
Q: Q1) Air at Mach number 2.0, pressure of 80kPa and temperature of 280K is flowing through a…
A:
Q: Q2. Correct the false statement. 1) An oblique shock wave is always parallel to the incoming flow.…
A: 1. An oblique shock wave is inclined with respect to incident upstream flow direction.
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: 78. 5.23. Assume that a supersonic nozzle operating isentropically delivers air at an exit Mach…
A:
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.
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: A large tank, at 500 K and 200 kPa, supplies isentropicairfl ow to a nozzle. At section 1, the…
A: Given
Q: 5 Consider the subsonic flow through a divergent duct with area ratio A2/A, 1.7. If the inlet…
A:
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: 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: Q3: Air flow over a blunt nosed body. The air flow un the free stream a head of the body has a Mach…
A: Given: The mach number before shock, Mx = 1.5 The static pressure before shock, Px = 40 kPa The…
Q: Identify which of the following is the correct formula for Mach number: TAS - constant Ма IAS b. M =…
A:
Q: Q1) Air at mach number 2 over a wedge and generation of an oblique shock wave 40° . determine : 1.…
A:
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: An aircraft cruises at 12 km altitude on a standard day. A pitot tube mounted on the aircraft…
A: Given: Altitude=12km Stagnation pressure P0=84.3kPa
Q: Supersonic airflow takes a 5° expansion turn, as inFig. Compute the downstream Mach number…
A:
Trending now
This is a popular solution!
Step by step
Solved in 2 steps with 2 images
- Air with stagnation pressure of 800 kPa and temperature of 100⁰C ,is expanded isentropically to the channel 1 where A₁ = 20 cm² and P₁ 47 kPa. Count: a. Ma1 b. The area of the throat / neck (the narrow part) of the channel c. Mass flow rate m d. In part 2 which is located between the throat/neck with part 1, where the area of part 2 is 9 cm² ,calculate Ma2How do I find reservoir pressure given the exit-to-throat area ratio of a supersonic nozzle and a Pitot tube measurement from the test section.A dry gas well equipped 30 MMcfd with 85psig tubing pressure must be compressed to 300 psig for sales by centrifugal compressor design What is the amount of actual power required to perform this job, estimate the minimum number of compression stages required for optimum compression efficiency? Additional data nsty = 0.069 cuft , suction temperature 85 K = 1.2 . theoretical speed N - 12200 rpm average deviation factor -0.85atmospheric pressure (assumed xd)=14.71 psia
- The Allis-Chalmers D30LR centrifugal compressor delivers33,000 ft3/min of SO2 with a pressure change from 14.0 to18.0 lbf/in2 absolute using an 800-hp motor at 3550 r/min.What is the overall efficiency? What will the flow rate andDp be at 3000 r/min? Estimate the diameter of the impeller.A converging–diverging nozzle with a 4:1 exit-area ratioand p0 = 500 kPa operates in an underexpanded condition as in Fig. The receiver pressureis pa = 10 kPa, which is less than the exit pressure sothat expansion waves form outside the exit. For the givenconditions, what will the Mach number Ma2 and the angleϕ of the edge of the jet be? Assume k = 1.4 as usual.What is the theorical fan power needed to develop a pressure of 7.5 cm water gage W.G. supplied to air moving at 6.0 meter/min through a round duct of 880 mm in diameter?
- The large compressed - air tank shown in the figure bellow exhausts from a nozzle at an exit velocity of Ve = 235 m / s. Assuming isentropic flow, compute: a) the exit Mach number. b) the pressure in the tank. (take; k = 1.396, Cp = 917 J / Kg.k and R = 260 J / Kg.k) air at 30 ° C tank conditions remain constant Pate = 101 kPaAssuming the clearance is negligible for a single stage compressor with the followingdata.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/minTake “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1. What is the power input to the compressor if compression is isentropic in kW to 3 decimal places? 2. What is the power input to the compressor in kW to 3 decimal places if the compression reversible isothermal?Assuming the clearance is negligible for a single stage compressor with the following data.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/min Take “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1.What is the power input to the compressor if compression is isentropic in kW to 3 decimal places?
- 1. Assume a horizontal shaft handling water at 65 deg C (Pv=2.503 KPa, Density=980.5 m3/kg). The suction nozzle is 4.35 m below the pump centerline and the pressure gauge reading at this point is 221Kpag. Determine the NPSHa if the head loss is 0.82 m. If the NPSHr is 3m less than the NPSHa you got on question number 1, determine the pump suction specific speed at pump rotating at 1800rpm and Q=500gpmEach stage of an axial flow compressor is of 0.5 reaction, has the same mean blade speed and the same flow outlet angle of 30 degree relative to the blades. The mean flow coefficient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m. Using compressible flow analysis determine the axial velocity and the mass flow rate.The general energy balance equation for a turbine is: Qnet + Wnet = ΔmH + ΔKE + ΔPE What does it mean when the term ΔmH is negative? Describe what changes occured to the fluid's energy, and where it went.