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Throat area of 0.25m2 and exit to throat area ratio (Ae/At) of 35.5 are measured to be 1500 kPa a...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet sta...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po)...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po) and temperature (To) are equal to 5 atm and 600K, respectively. Determine exit Mach number, temperature and pressure values for normal shock at 3/4 of the diverging portion.
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25...
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25 as shown below. The stagnation pressure upstream of the throat is 8.5 atm and the stagnation temperature is 1000 K. (a) Assume the air is expanded isentropically to supersonic speed at the exit. Determine the following properties at the nozzle exit: Me, Pe, Te, Pe, ue, Poe, Toe (b) If the area ratio in the subsonic part of the converging diverging nozzle, A1/A is...
Air with a stagnation pressure of 1000 kPa and stagnation temperature of 500 K flows isentropically into a 100 kPA ambient (back) pressure. Calculate the Area ratio at the exit of a nozzle for isentro...
Air with a stagnation pressure of 1000 kPa and stagnation temperature of 500 K flows isentropically into a 100 kPA ambient (back) pressure. Calculate the Area ratio at the exit of a nozzle for isentropic flow with these conditions. Further if flow is considered isentropic within the nozzle calculate the isentropic nozzle efficiency if the area ratio at the nozzle exit were 1.2 rather than your calculated value for isentropic exit conditions above.
Fundamentals-of-Compressible-Fluid-Dynamics Balachandran CHAPTER 4 6. A conical diffuser of 15 cm...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandran CHAPTER 4 6. A conical diffuser of 15 cm has an area ratio of 4. If the pressure, temperature and velocity at the inlet section are 0.69 bar, 340 K and 180 m/s, estimate the exit pressure and exit velocity. What will be the change in impulse function. [Ans. p2 = 0.8074 bar; V2 = 45 m/s; F2 - F1 = 4167.5 N] 7. The Mach number at inlet and exit of a supersonic diffuser are 3 and...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po) and temperature (To) are equal to 5 atm and 600K, respectively. Determine exit Mach number, temperature and pressure values for normal shock at 3/4 of the diverging portion.
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25 as shown below. The stagnation pressure upstream of the throat is 8.5 atm and the stagnation temperature is 1000 K. (a) Assume the air is expanded isentropically to supersonic speed at the exit. Determine the following properties at the nozzle exit: Me, Pe, Te, Pe, ue, Poe, Toe (b) If the area ratio in the subsonic part of the converging diverging nozzle, A1/A is...
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