Q2: Helium, at To = 400 K, enters a nozzle isentropically. At section 1, where A1 = 0.1 m2, a pitot-static arrangement (see Fig. Q2) measures stagnation pressure of 150 kPa and static pressure of 123 kPa. Estimate (a) M1; (b) Tị; (c) mass flow; and (d) A*. Take y = 1.66 and R = 2077 J/(kg-K). Air at 100 K Mercury Ans. (a) 0.5; (b) 370 K; (c) 9.03 kg/s; and (d) 0.0756 m².

Q2: Helium, at To = 400 K, enters a nozzle isentropically. At section 1, where A1 = 0.1 m2, a pitot-static arrangement (see Fig. Q2) measures stagnation pressure of 150 kPa and static pressure of 123 kPa. Estimate (a) M1; (b) Tị; (c) mass flow; and (d) A*. Take y = 1.66 and R = 2077 J/(kg-K). Air at 100 K Mercury Ans. (a) 0.5; (b) 370 K; (c) 9.03 kg/s; and (d) 0.0756 m².

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

In Fig. water exits from a nozzle into atmosphericpressure of 101 kPa. If the fl ow rate is 160 gal/min and frictionis neglected, what is the gage pressure at section 1?( a ) 1.4 kPa, ( b ) 32 kPa, ( c ) 43 kPa, ( d ) 29 kPa, ( e ) 123 kPa
Consider the venturi nozzle of Fig. , with D = 5 cmand d = 3 cm. Stagnation temperature is 300 K, and theupstream velocity V1 = 72 m/s. If the throat pressure is124 kPa, estimate, with isentropic flow theory, (a) p1,(b) Ma2, and (c) the mass flow.
Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of 30,000-ft, assuming weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ??? = 0.015, and K = 0.08 a. The thrust required at 30,000-ft. (in pounds)
1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a duct where A₁ = 20 cm² and p₁ = 47 kPa. Compute ( a ) Ma₁ , ( b ) the throat area , and ( c ) m . At section 2 between the throat and section 1, the area is 9 cm². (d) Estimate the Mach number at sec tion 2. Plz sketch and solve it
Q2 (a) In designing a nozzle why nozzle angle is not zero. Explain with the help of sketch. Q2 (b) In designing a nozzle, what is the significance of stagnation properties? Q2 (c) During Steam turbine construction, what is the purpose of shroud ring?
Air flows isentropically through a variable-area duct. Atsection 1, A1= 20 cm2, p1= 300 kPa, ρ1= 1.75 kg/m3, andMa1= 0.25. At section 2, the area is exactly the same, butthe flow is much faster. Compute (a) V2, (b) Ma2, (c) T2,and (d ) the mass flow. (e) Is there a sonic throat betweensections 1 and 2? If so, find its area.
Helium, at T0 = 400 K, enters a nozzle isentropically. Atsection 1, where A1 = 0.1 m2, a pitot-static arrangement(see Fig. P9.25) measures stagnation pressure of 150 kPaand static pressure of 123 kPa. Estimate (a) Ma1, (b) massfl ow m # , (c) T1, and (d ) A*.
Air flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock stands at section 2. Compute (a) the mass flow,(b) the Mach number, and (c) the stagnation pressure atsection 3.
A typical carbon dioxide tank for a paintball gun holdsabout 12 oz of liquid CO2. The tank is fi lled no more thanone-third with liquid, which, at room temperature, maintainsthe gaseous phase at about 850 psia. (a) If a valve isopened that simulates a converging nozzle with an exitdiameter of 0.050 in, what mass fl ow and exit velocityresults? (b) Repeat the calculations for helium.
A large tank, at 500 K and 200 kPa, supplies isentropicairfl ow to a nozzle. At section 1, the pressure is only 120kPa. What is the Mach number at this section?(a) 0.63, (b) 0.78, (c) 0.89, (d ) 1.00, (e) 1.83 assume one-dimensional fl ow of ideal air, R 5287 J/(kg ? K) and k 5 1.4.
The convergent-divergent nozzle in Figure 22 expands and accelerates dry air to supersonic speeds at the outlet, where p2 = 8kPa and T2 = 240K. At the throat p1 = 284 kPa, T1 = 665 K and V1 = 517 m / s. Assuming steady and compressible flow of an ideal gas, estimate (a) the mass flow wn kilograms per hour, (b) the velocity V2, and (c) the match number Ma2
The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic speeds at theexit, where p 2 = 8 kPa and T 2 = 240 K. At the throat, p 1=284 kPa, T 1 = 665 K, and V 1 = 517 m/s. For steadycompressible fl ow of an ideal gas, estimate ( a ) the mass fl owin kg/h, ( b ) the velocity V 2 , and ( c ) the Mach number Ma 2 .